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UNCLASSIFIED Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiyff and S. M. Henbest Aerospace Division Defence Science and Technology Organisation DSTO–TR–2898 ABSTRACT Experimental skin-friction and pressure-coefficient data for a generic scale- model submarine, tested in the Low-Speed Wind Tunnel at DSTO, are pre- sented. The effect on skin-friction and pressure coefficients due to different sizes and types of boundary layer tripping devices, including the case of no tripping device, was investigated for the Reynolds number range of 3.58 × 10 6 to 6.27 × 10 6 , where the Reynolds number is based on model length. Skin friction was measured using the Preston-tube method which is a technique applicable to turbulent boundary layers only. For the laminar and transition regions the Preston tube only provided qualitative results. The results demon- strate the importance of correctly tripping the boundary layer and provide a guide on determining the size and type of tripping device required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-stream velocity. While the results are specific to the model geometry tested and for the given trip location, the methodology is applicable to other general model ge- ometries and trip locations. This report does not address the difficult problem of where to place the trip. APPROVED FOR PUBLIC RELEASE UNCLASSIFIED

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Page 1: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED

Skin-Friction Measurements on a Model

Submarine

M B Jones L P Erm A Valiyff and S M Henbest

Aerospace Division

Defence Science and Technology Organisation

DSTOndashTRndash2898

ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine tested in the Low-Speed Wind Tunnel at DSTO are pre-sented The effect on skin-friction and pressure coefficients due to differentsizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358 times 106

to 627 times 106 where the Reynolds number is based on model length Skinfriction was measured using the Preston-tube method which is a techniqueapplicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demon-strate the importance of correctly tripping the boundary layer and provide aguide on determining the size and type of tripping device required to achievea correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for thegiven trip location the methodology is applicable to other general model ge-ometries and trip locations This report does not address the difficult problemof where to place the trip

APPROVED FOR PUBLIC RELEASE

UNCLASSIFIED

DSTOndashTRndash2898 UNCLASSIFIED

Published by

DSTO Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

Telephone (03) 9626 7000Facsimile (03) 9626 7999

ccopy Commonwealth of Australia 2013AR No AR 015-744October 2013

APPROVED FOR PUBLIC RELEASE

ii UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Skin-Friction Measurements on a Model Submarine

Executive Summary

A series of experiments have been conducted in the Low-Speed Wind Tunnel at DSTO us-ing a generic submarine model (135 m long) to investigate the effect of different boundary-layer tripping devices1 on the skin-friction and pressure coefficients on the model Theresults also provide a reference data set to assist in the development and validation ofcomputational-fluid-dynamics codes

The submarine model tested was in a ldquobare-hullrdquo configuration aligned with the flowdirection The skin-friction was measured using a fine Pitot tube placed on the surface ofthe hull A Pitot tube used in this way is referred to as a Preston tube and the techniqueis applicable in regions where the boundary layer is in a turbulent state For regionswhere the boundary layer is laminar the Preston tube does not give quantitatively correctskin-friction values However the Preston tube was found to provide a useful means ofdetermining the location of the laminar to turbulent transition point

The results show the importance of correctly tripping the boundary layer and providea guide for selecting the size and type of tripping device required to achieve a correctly-stimulated turbulent boundary layer for a given wind tunnel velocity Only a limitedrange of trip sizes and types were tested but it was found that a trip wire of diameter02 mm or grit of size 80 give a correctly stimulated boundary layer However of these twodevices the wire is the preferred option since it was observed that grit may erode duringa testing program It is recommended that further work be carried out to quantify theskin friction in the laminar flow regions and the analysis be extended to other trip typessuch as cylindrical pins

The location of the tripping device was fixed relative to the model and this report doesnot address the difficult problem of where to place the trip

1A tripping device is used to force the boundary layer to transition from a laminar to turbulent state

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DSTOndashTRndash2898 UNCLASSIFIED

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iv UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Authors

Malcolm JonesAerospace Division

Malcolm Jones obtained a Bachelor of Engineering (Mechani-cal) degree in 1994 and a PhD in 1998 both from The Uni-versity of Melbourne His PhD involved an experimental andtheoretical study of a turbulent boundary layer developing in anaccelerated flow He joined the Defence Science and TechnologyOrganisation in 2007 where he is currently employed as a Re-search Scientist in Aerospace Division While at DSTO he hasbeen involved in aerodynamic testing of aircraft models such asthe F-35 and AP-3C in the Low Speed Wind Tunnel aeroacous-tic measurements and analysis of cavity flows and aerodynamicand structural measurements of flapping wings Prior to joiningDSTO he was employed as Research Fellow and then lecturerin the Department of Mechanical Engineering at The Univer-sity of Melbourne (1999-2003) From 2004-2007 he worked atthe School of Mathematical Sciences Queensland University ofTechnology During his academic appointments he gave lec-ture courses in fluid mechanics heat transfer manufacturingand mathematics and undertook research in turbulent bound-ary layer flows and biological fluid mechanics

UNCLASSIFIED v

DSTOndashTRndash2898 UNCLASSIFIED

Lincoln ErmAerospace Division

Lincoln Erm obtained a Bachelor of Engineering (Mechanical)degree in 1967 and a Master of Engineering Science degree in1969 both from the University of Melbourne His Masterrsquos de-gree was concerned with the yielding of aluminium alloy whensubjected to both tensile and torsional loading He joined theAeronautical Research Laboratories (now called the DefenceScience and Technology Organisation) in 1970 and has workedon a wide range of research projects including the prediction ofthe performance of gas-turbine engines under conditions of pul-sating flow parametric studies of ramrocket performance flowinstability in aircraft intakes and problems associated with thelanding of a helicopter on the flight deck of a ship Concurrentlywith some of the above work he studied at the University ofMelbourne and in 1988 obtained his Doctor of Philosophy de-gree for work on low-Reynolds-number turbulent boundary lay-ers Since this time he has undertaken research investigationsin the low-speed wind tunnel and the water tunnel Recentwork has been concerned with extending the testing capabili-ties of the water tunnel including developing a two-componentstrain-gauge-balance load-measurement system for the tunneland developing a dynamic-testing capability for the tunnel en-abling aerodynamic derivatives to be measured on models

Aliya ValiyffAerospace Division

Aliya Valiyff graduated from the University of Adelaide in 2009with a Bachelor of Aerospace Engineering and Bachelor of Sci-ence (Applied Mathematics and Physics) with 1st class honoursShe commenced work with DSTO in 2010 and during her timeshe has mainly worked within the Unmanned Aerial System -Corporate Enabling Research Programme (CERP) undertak-ing research on flapping wing and the flight and the UnderseaWarfare- CERP

vi UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Simon HenbestAerospace Division

Simon Henbest obtained a Bachelor of Engineering (Mechan-ical) degree with honours in 1977 and a PhD in 1983 bothfrom The University of Melbourne His PhD titled rdquoThe Struc-ture of Turbulent Pipe Flowrdquo provide experimental support toTownsendrsquos attached eddy hypothesis for wall bounded flowsIn 1984 he was awarded an Australian National Research Fel-lowship and continued wall turbulence research at the Univer-sity of Melbourne In 1987 he commenced employment at theAeronautical Research Laboratories (now called the DefenceScience and Technology Organisation) and obtained merit pro-motions to both Senior Research Scientist and Principal Re-search Scientist While at DSTO he has been involved in re-search into high speed jet and aeroacoustic cavity flows the IRsignature prediction of aircraft numerous aerodynamic testingprogrammes He has acted as a Research Leader for extendedperiods in AVD AOD and HPPD He is currently Head of FluidMechanics in Aerospace Division

UNCLASSIFIED vii

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viii UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Contents

Glossary xi

Notation xi

1 Introduction 1

11 Boundary-Layer Transition 1

12 Approach of Erm amp Joubert (1991) 2

13 Empirical Expressions to Determine Sizes of Tripping Devices 4

2 Preston-Tube Method of Measuring Skin-Friction Coefficients 4

3 Test Program 7

31 Test Facility 7

32 Test Model 7

33 Tripping Devices 10

34 Pressure Scanners 10

35 Data Acquisition Software 12

36 Experimental Procedure 12

37 Data Reduction 13

4 Results 14

41 Skin Friction Without a Tripping Device 14

42 Skin Friction With Tripping Devices 16

421 Comparison of the Different Trip Devices 21

422 Scaling of Skin Friction with Reynolds Number 22

423 Over-stimulation and the Maximum Trip Reynolds Number 23

43 Pressure Coefficients 24

44 Pressure Gradients 26

5 Comparison with CFD Predictions 29

6 Conclusions 30

7 Acknowledgements 32

Appendices

UNCLASSIFIED ix

DSTOndashTRndash2898 UNCLASSIFIED

A Summary of Tripping Devices Used in Previous Experiments 35

B Preston Tube Data Processing 36

C Skin Friction Coefficients 37

D Pressure Coefficients 45

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UNCLASSIFIED DSTOndashTRndash2898

Glossary

DARPA Defense Advanced Research Projects AgencyCERP Corporate Enabling Research ProgramCFD Computational Fluid DynamicsLSWT Low-Speed Wind TunnelDSTO Defence Science and Technology Organisation

Notation

Cf Local skin-friction coefficientCp Pressure coefficientd Outer diameter of Preston tubedT Diameter of trip wireh Height of grit transition strippinfin Free-stream static pressurepp Total pressure of Preston tubeps Model surface static pressurept Free-stream total pressurep+x Non-dimensional pressure gradient parameterRe Reynolds numberRedT Reynolds number based on diameter of wireRex Reynolds number based on the stream-wise coordinateRext Streamwise Reynolds number of transition pointU Streamwise velocity in boundary layerU1 Streamwise velocity at edge of boundary layerUinfin Nominal streamwise velocity in tunnel working-sectionUτ Friction velocityw Width of grit transition stripx Streamwise coordinatext Streamwise coordinate of transition pointy Wall normal coordinate∆p ∆p = pp minus psν Kinematic viscosityρ Fluid densityτ0 Wall shear stress

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DSTOndashTRndash2898 UNCLASSIFIED

THIS PAGE IS INTENTIONALLY BLANK

xii UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

1 Introduction

This work aims to understand flow fields about a submarine As part of this programa series of experiments have been conducted in the Low-Speed Wind Tunnel (LSWT) atthe Defence Science and Technology Organisation (DSTO) to quantify the skin-frictiondistributions on a generic submarine model and in the process investigate the effectivenessof a limited range of tripping devices The results also provide a reference data set forcomputational fluid dynamics (CFD) validation of a submarine model

When conducting tests in wind tunnels on a sub-scale model for results of the exper-iment to be transferable to the full-scale vehicle the flow patterns and load coefficientson the model and the full-size vehicle need to be made similar Ideally this is achievedthrough matching the Reynolds number of the flow over the model to that of the full-scalevehicle However in practice this is difficult to achieve and is not always possible To en-sure that the flow features on the model are representative of those for the full-size vehiclea tripping device can be used such that the boundary layers (ie regions of laminar flowlaminar-to-turbulent transition and turbulent flow) are made similar However differenttripping devices can impart different disturbances into the flow In order to correctly stim-ulate the boundary layer on the submarine model and avoid over- or under-stimulationthe type and size of tripping devices need to be selected for a given Reynolds numberor Reynolds number range and also for a specific trip location Additionally the chosentripping device will be specific to a given tunnel and would be dependent on factors suchas the level of free-stream turbulence in the tunnel

dT

Ud

Trip wire

xd

Laminar Transition Turbulent

Boundary-layeredge

U1

Figure 1 Diagrammatic representation of a boundary layer being tripped based on adiagram given by White (1974)

11 Boundary-Layer Transition

Boundary-layer transition is a complicated physical process dependent on instability mech-anisms including Tollmien-Schlichting waves crossflow and Gortler instabilities (see Reedamp Saric 2008) Over the years there have been numerous articles published on transi-tion both from experimental investigations and CFD analyses in low-speed transonic

UNCLASSIFIED 1

DSTOndashTRndash2898 UNCLASSIFIED

and hypersonic flow regimes (for example Schlatter amp Henningson 2009) Details of thetransition process are still not fully understood In the present report transition physicalprocesses are not considered instead attention is focused on how to stabilise the posi-tion of the transition using a tripping device and to ensure that the turbulent boundarylayer is neither under- or over-stimulated irrespective of the flow physics associated withtransition

12 Approach of Erm amp Joubert (1991)

A diagrammatic representation of a boundary layer being tripped is shown in Figure 1where dT is the height of the tripping device U1 is the streamwise velocity at the edge ofthe boundary layer xd is the location of the tripping device measured from the nose ofthe model and Ud is the velocity in the boundary layer at the top of the device

A question that had to be addressed was what is the best size and type of trippingdevice to use in the current experiments in the LSWT to trip the boundary layer on thesubmarine model Erm amp Joubert (1991) faced a similar question in their studies on low-Reynolds-number flows over a smooth flat surface in a zero pressure gradient For differenttypes of tripping devices they measured longitudinal skin-friction coefficients for a rangeof free-stream velocities Their data for a 12 mm wire tripping device are reproduced inFigure 2 From this figure it can be seen that as the velocity is increased from 8 ms thedevice imparts an increased amount of turbulent energy into the flow so that the laminar-to-turbulent transition region moves upstream They conjectured that correct stimulationis associated with a particular curve when the peaks of successive curves correspondingto higher velocities do not advance significantly upstream Velocities lower than thatcorresponding to the particular curve were obviously associated with under-stimulatedflows since the peaks of the curves were well downstream of the device and thus thedevice was therefore not completely effective in tripping the flow Since the velocitycorresponding to the particular curve establishes a turbulent boundary layer almost to thepossible upstream limit of turbulent flow it seemed reasonable to assume that the maineffect of higher velocities was to overstimulate the flow

The x-coordinate corresponding to the peaks of Figure 2 are plotted in Figure 3 as afunction of streamwise velocity and it is apparent that the above condition for correct stim-ulation was satisfied when the velocity was between 10 and 12 ms This corresponds to aminimum Reynolds number of the tripping device in the range of RedT = U1dT ν = 800to 960 where ν is the kinematic viscosity For the case where a trip device has aReynolds number greater than the minimum required the tripping device may overstim-ulate the flow Note over-stimulation does not necessarily result in higher skin-frictionwhen compared to a correctly stimulated layer Rather it means that the disturbanceintroduced by the tripping device is felt downstream of the transition region and leadsto a ldquonon-standardrdquo turbulent boundary initially developing Ideally to assess whetherover-stimulation has occurred complete velocity profiles in the turbulent region need tobe measured and compared against reference data sets such as those collated by Coles(1962)

It should be noted that in the current work the boundary layer develops in a pressuregradient with wall curvature in both the streamwise and spanwise directions Whereas

2 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

the work of Erm amp Joubert (1991) was undertaken on a flat plate zero pressure gradientthis means the RedT values given above cannot be applied directly to predict the trip sizerequired However the approach taken here broadly follows that of Erm amp Joubert (1991)in that a range of trip Reynolds numbers were tested (by varying both freestream velocityand trip size) and the skin-friction downstream of the trip measured

0 01 02x (m)

03 04 05

Figure 2 Cf vs x measurements for a 12 mm diameter trip wire for different free-streamvelocities as obtained by Erm amp Joubert (1991)

8 9 10 11 12 13 14

xlocation

(m)of

peakCf

Location of peak Cf

Location of trip device

01

02

0

Uinfin (ms)

Figure 3 Location of the peak Cf values shown in Figure 2

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DSTOndashTRndash2898 UNCLASSIFIED

13 Empirical Expressions to Determine Sizes of TrippingDevices

Researchers have proposed different empirical expressions for determining the size of deviceto use to trip the flow The relationships incorporate parameters including the height ofthe tripping device dT the velocity at the edge of the boundary layer U1 the velocity inthe undisturbed boundary layer at the top of the device Ud and the wall friction velocityevaluated at the device Uτ The friction velocity is defined by τ0 = ρU2

τ where τ0 is thesurface shear stress and ρ is the fluid density Recommendations for fully-effective trippingcover quite a wide range Tani et al (1940) proposed the criterion UτdT ν = 13 Fage ampPreston (1941) proposed UτdT ν = 20 Braslow amp Knox (1958) proposed UddT ν = 600and Gibbings (1959) proposed U1dT ν = 826 It should be noted that the criterion ofGibbings (1959) is based on a review of many data sets included those of Tani amp Sato(1956) and Fage amp Preston (1941) Gibbings (1959) expresses the Tani amp Sato (1956)and Fage amp Preston (1941) criteria as Reynolds numbers based on the freestream velocitywhich gives values of U1dT ν = 600 and 840 respectively The criterion given aboverepresent minimum values of the tripping device Reynolds number required to correctlytrip the boundary layer and agree with the results of Erm amp Joubert (1991)

An analysis of the literature for tests done on bodies of revolution indicated that thereis no consistent approach for selecting the size and type of device to use on such bodiesAppendix A gives details of devices used by different investigators for bodies of revolutiontogether with other experimental information Based on the freestream velocity and tripheight the Reynolds numbers of the trip devices given in Appendix A range from 200 to40 times 103 For the present investigation the approach used to establish the effects thatdifferent devices had on tripping laminar boundary layers was similar to that used byErm amp Joubert (1991) for a smooth flat plate in a zero pressure gradient Using theirtechnique it is possible to establish the size and type of tripping device to be used for agiven velocity to obtain correctly stimulated turbulent boundary layers

2 Preston-Tube Method of Measuring

Skin-Friction Coefficients

Skin-friction coefficients in a turbulent boundary layer flowing over a smooth surface canbe measured in a number of different ways (Fernholz et al 1996) including using Prestontubes (Preston 1954) from velocity profiles and using devices mounted flush with thesurface of a model Of the alternative approaches the Preston-tube method is convenientand is widely used The method makes use of a simple Pitot tube placed on the surfaceof a body and when used this way it is termed a Preston tube The method depends onan underlining assumption that in the region adjacent to the surface the flow is primarilydetermined by the surface shear stress and the properties of the fluid and is independentof factors such as pressure gradient and surface curvature The assumption implies thatthe velocity profile in a turbulent boundary layer adjacent to the surface is given by

U

Uτ= f

(Uτy

ν

)(1)

4 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

where U is the local stream-wise velocity Uτ is the friction velocity f is a universalfunction y is the wall normal coordinate and ν is the kinematic viscosity Equation (1) isoften referred to as the ldquolaw of the wallrdquo (Coles 1956)

A Pitot tube placed on the wall will measure a pressure relative to the wall staticpressure of ∆p = ρU22 at an effective coordinate y = c0d where d is the outer diameterof the Pitot tube and c0 is an unknown constant Substituting the values U =

radic(2∆pρ)

and y = cod into (1) yields a relationship between the wall shear stress fluid propertiesPreston-tube pressure difference and the tube diameter which is given by

2∆p

ρUτ2 =

[f

(Uτ c0d

ν

)]2 (2)

Alternatively for the purpose of measuring skin friction (2) can be expressed more con-veniently in the form

τ0d2

4ρν2= F

(∆pd2

4ρν2

)(3)

where c0 has been absorbed into the function F The function F represents the ldquocalibra-tionrdquo function for a Preston tube and several experimentally derived forms exist in theliterature (see Preston 1954 Patel 1965 Zagarola et al 2001) Generally the calibrationis determined by placing the Preston tube in a pipe flow where the wall shear stress (orfriction factor) can be determined accurately by measuring the pressure gradient in thepipe

For the data presented in this report the calibration of Patel (1965) was used todetermine the wall shear stress The calibration curve of Patel (1965) is given as follows

xlowast =ylowast + 2 log10(195ylowast + 410) for 55 ltUτd

2νlt 800 (4)

ylowast =08287 minus 01381xlowast + 01437xlowast2 minus 0006xlowast3 for 56 ltUτd

2νlt 55 and (5)

ylowast =1

2xlowast + 0037 for

Uτd

2νlt 56 (6)

where

xlowast = log10

(∆pd2

4ρν2

)and ylowast = log10

(τ0d

2

4ρν2

)

The local skin friction coefficient Cf is then found using

Cf =τ0

12ρU

21

(7)

where U1 is the streamwise velocity at the edge of the boundary layer

The calibration given by (4)-(6) is valid only for a hydrodynamically smooth surfaceA surface is considered hydrodynamically smooth provided that the height of surfaceroughness elements remain less than 5νUτ (Jimenez 2004) The minimum value of 5νUτthat was measured was approximately 4microm and the measured surface finish was found tobe an order of magnitude less than this value (Section 32) Hence the requirement of ahydrodynamically smooth surface is satisfied for this experiment

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DSTOndashTRndash2898 UNCLASSIFIED

The fundamental requirement for using a Preston tube is that the boundary layer isin a turbulent state and that the dimension of the Preston tube is such that it remainswithin the region where (1) is valid (ie from (4) Uτdν lt 1600) The diameter of thePreston tube for all experiments was d = 06 mm and this ensured that Uτdν remainedless than 1600 well within the range of the calibration (4)

It is known that for sufficiently strong pressure gradients the form of (1) changes (seeNickels 2004) Patel (1965) quantifies the effect of pressure gradients using the non-dimensional pressure gradient parameter1

p+x =ν

ρU3τ

dp

dx (8)

The error associated with using a Preston tube in pressure gradients is quantified by Patel(1965) and is given by the following inequalities

1 Adverse pressure gradient

Max Error 3 0 lt p+x lt 001 andUτd

νle 200 (9a)

Max Error 6 0 lt p+x lt 0015 andUτd

νle 250 (9b)

2 Favourable pressure gradient

Max Error 3 minus0005 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10a)

Max Error 6 minus0007 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10b)

The pressure gradient data are presented in Section 44 and were found to fall within thelimits of (9a) and (10a) indicating that the skin-friction coefficients are valid to withinplusmn3 This accuracy is similar to the alternative direct skin-friction measuring techniqueswhich typically achieve an accuracy of plusmn4 (Fernholz et al 1996)

The effect of model spanwise curvature on (4)-(6) is not quantified A reasonableassumption is that since the boundary layer thickness is much less than the model diameterthe effect of spanwise model curvature can be neglected

The Preston-tube method as outlined above requires that the boundary layer is in aturbulent state For this reason the method cannot be used to infer the skin friction atlocations were the boundary layer is in a laminar state However the ∆p values read by thePreston tube can be used to determine where laminar-to-turbulent transition occurs Theregion of transition is associated with a discontinuity in ∆p when plotted as a functionof streamwise coordinate x as shown by Erm amp Joubert (1991)

1for clarity we have adopted the notation for the pressure gradient parameter used by Nickels (2004)Patel (1965) uses the symbol ∆

6 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 4 LSWT Layout see Erm (2003)

3 Test Program

In this preliminary investigation four different tripping devices were used to investigatethe effect of the device on the skin-friction profile of a generic sub-scale submarine modelTests were conducted both with and without the tripping devices at a range of nominalfree-stream velocities Uinfin ranging from Uinfin = 40 to 70 ms to assess their effectivenessin tripping the boundary layer

31 Test Facility

The Low-Speed Wind Tunnel at DSTO is a closed circuit continuous flow tunnel with acontraction ratio of 41 The test section has an irregular octagonal shape with a heightof 213 m a width of 274 m and a length of 6553 m with a longitudinal turbulenceintensity of approximately 04 in the region where the models are tested (see Erm2003) An outline of the plan of the wind tunnel is shown in Figure 4 Free-streamvelocities were measured using static pressure rings at the upstream and downstreamends of the contraction A Pitot-static probe mounted on the side wall near the front ofthe working section was used to provide an independent measurement of the free-streamvelocity

32 Test Model

The sub-scale submarine model utilised in these tests is referred to as the Joubert modelsince the geometry is based on the work of Joubert (2004) and Joubert (2006) as well asLoid amp Bystrom (1983) The model was designed for the purpose of experimental and

UNCLASSIFIED 7

DSTOndashTRndash2898 UNCLASSIFIED

1

2 345

6 7 8 91011

12 13 141516

17 181920

212223

24 252627

28 29 303132

33 34

35

Top view

Side view

Figure 5 Schematic of scale model showing static-pressure port locations green and redmarkers represent the starboard and port static-pressure ports respectively

numerical studies and has no full-scale equivalent While the full model includes a casingcentre fin and control surfaces all tests reported here were conducted on the axisymmetricbody shape only

The model was machined from aluminum and consists of an ellipsoidal nose a cylin-drical centre-body and a streamlined tail section At the design stage an N6 surface finishwas specified for the model which corresponds to a roughness of 08microm in waviness Af-ter manufacture the surface finish was checked using a Surface Roughness Indicator andthe finish was found to be better than the design specification The model was anodisedwhich increased the thickness of the natural oxide layer by about 10microm

The model is 1350 mm long with a maximum diameter of 185 mm and slendernessratio of 73 where the slenderness ratio is defined as hull length divided by maximumhull diameter The model contains 21 longitudinal static-pressure ports on the centre-lineof the upper surface and 14 lateral static-pressure ports offset to the port and starboardsides of the upper surface centre-line Figure 5 shows the stream-wise location of thestatic-pressure ports

The model was supported by a single pylon as shown in Figure 6 All tests were carriedout at zero angle of yaw and zero angle of pitch The origin of the body coordinate systemis located at the nose of the submarine model The x-axis corresponds to the axis ofsymmetry of the model

8 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 6 Submarine model mounted in LSWT showing pylon support and pitch controlarm

UNCLASSIFIED 9

DSTOndashTRndash2898 UNCLASSIFIED

Table 1 Details of tripping devices where the Reynolds number is based on the height ofthe device The minimum Reynolds number and maximum Reynolds number correspondto nominal freestream velocities of Uinfin = 40 ms and Uinfin = 70 ms respectively where his the height of the grit and w is the width of the grit

Device Dimensions (mm) RedT (min) RedT (max)

Wire 1 dT = 01 281 496Wire 2 dT = 02 577 1015Wire 3 dT = 05 1443 256680 Grit h = 021 w = 3 605 1073

33 Tripping Devices

In this work four tripping devices were tested and consisted of circular wires with diame-ters dT = 01 02 and 05 mm as well as a distributed silicon carbide grit of size 80 havinga width of 3 mm The circular wires were bent to conform to the local diameter of thesubmarine and then attached with ldquosuper-gluerdquo such that there was no gap between thewire and the model surface Figure 7 The silicon carbide grit is prepared by distributinga layer of grit on double-sided sticky tape the tape is then adhered to the submarineFigure 8 The tripping devices were attached to the submarine model circumferentiallylocated at a streamwise coordinate of x = 675 mm measured from the nose of the sub-marine which corresponds to 5 of the total model length The dimensions of the tripdevices along with the Reynolds number range of the trip devices are summarised inTable 1 Note that the Reynolds number of the trip device is defined as RedT = U1dT νwhere for the case of the 80 grit dT is replaced by the grit height h

34 Pressure Scanners

Pressure Systems Incorporated (PSI) brand pressure scanners were used to measure allstatic and total pressures The pressure scanners are differential pressure measurementunits consisting of an array of silicon piezoresistive pressure sensors one for each pressureport The outputs of the sensors are electronically multiplexed through a single on-boardinstrumentation amplifier using binary addressing The scanners include a two-positioncalibration manifold actuated by momentary pulses of control pressures In the calibrateposition all sensors are connected to a common calibration pressure port A series ofaccurately-measured pressures is applied through this port to characterize the sensorsProper and periodic on-line calibration maintains static errors within plusmn003 or betterof the full-scale pressure range

The pressure scanners are controlled and sampled using a PSI 8400 electronic measure-ment system It is a modular parallel processing system for high-speed pressure scanningat up to 20000 measurements per second and allows the use of digitally temperaturecompensated pressure scanners

Two differential pressure scanners were used in the experiments All pressures aremeasured relative to the free-stream static pressure pinfin as measured by the referencefree-stream Pitot-static probe Each pressure scanner contained 32 ports The full-scale

10 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 7 Location of trip wire

Figure 8 Photo showing the 3 mm wide band of 80 grit transition strip

UNCLASSIFIED 11

DSTOndashTRndash2898 UNCLASSIFIED

pressure range of the scanners is 249 kPa (ldquo10 inches-of-water scannerrdquo) and 689 kPa(ldquo1 psi scannerrdquo) The 689 kPa scanner was used to read the static pressure at the longi-tudinal ports as well as the output from the Preston tube and the Pitot-static probe

For the purpose of cross-checking and for redundancy the Preston tube was connectedto two independent ports of the 689 kPa scanner and the two readings averaged For thisscanner pressures could be read to an accuracy of 6890 times 00003 Pa ie about 2 Pa Theminimum ∆p measured by the Preston tube was 145 Pa which gives a pressure scannerresolution of 14 However this minimum ∆p was recorded for a location where thePreston tube was in a laminar boundary layer and such data is only useful in a qualitativesense (see Section 2) For locations were the boundary layer is turbulent the minimum ∆pwas 340 Pa which gives a pressure scanner resolution of 06 The 249 kPa scanner wasused mainly to acquire the static pressures at the lateral ports

35 Data Acquisition Software

A software package called ImPressOne was used which communicates with the PSI 8400and displays and acquires the pressure data for the model under test For the staticpressure measurements 100 readings were acquired at each pressure port at a samplingrate of 20 Hz For the Preston-tube measurements the sample rate was increased and100 samples were acquired at each pressure port at a sampling rate of 50 Hz for eachfree-stream velocity

36 Experimental Procedure

The hull was tested with each of the selected tripping devices listed in Table 1 as wellas without a tripping device resulting in five different test configurations For each testconfiguration the static pressures were initially acquired for that particular configurationfollowed by the Preston-tube measurements

A Preston tube having a diameter of 06 mm was attached to the surface of the modelusing both plasticine and tape to ensure that the tube was positioned as flat as possibleon the surface of the model as shown in Figure 9 Preston-tube measurement were takenon the upper surface of the submarine model along a line directly above the centre-lineof the model For the dT = 02 and 05 mm wires and the grit case measurements weretaken from x = 73 mm to x = 1065 mm for a total of 18 stations For the dT = 01 mmwire measurements were limited to 3 stations between x = 305 mm and x = 442 mmThe stream-wise coordinates for the Preston tube measurements are given in the Table 2Data were acquired for a range of free-stream velocities from 40 to 70 ms in incrementsof 5 ms

For each nominal velocity the corresponding model Reynolds number was calcu-lated assuming standard temperature and atmospheric pressure conditions 20C and101 325 Pa respectively For each given test the temperature and static pressure of theair within the test section were logged and the air density and viscosity were calculatedTo account for daily variations in temperature and atmospheric pressure the freestream

12 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Flow direction

Figure 9 Preston tube located on the centre-line of the upper-surface of submarine

velocity was adjusted to ensure that the model Reynolds number remained constant foreach given nominal velocity condition as shown in Table 3

Table 2 Skin-friction measurement stations Where applicable the corresponding staticport number is given For the dT = 01 mm wire measurements were only taken at stations3050 3600 as well as an additional station at x = 4425 mm

xmm 731 787 843 900 1125 1350 1575 1800 2150Static port - - - 6 - 7 - 8 -

xmm 2500 3050 3600 5250 7000 8700 9500 10100 10650Static port 9 - 12 13 14 17 18 21 24

Table 3 Reynolds numbers (based on submarine length 135 m) corresponding to thenominal free-stream velocities

Nominal Uinfin 40 45 50 55 60 65 70 msRe 358 403 448 493 537 582 627 times106

37 Data Reduction

The static pressure readings from the pressure ports were converted to pressure coefficientsusing the relationship

Cp =ps minus pinfinpt minus pinfin

(11)

where pinfin is the reference free-stream static pressure pt is the reference free-stream totalpressure and ps is the static pressure on the surface of the submarine model

As explained in Section 34 all Preston tube pressures are measured relative to the free-stream static pressure In order to apply the Preston tube calibration (4)-(6) the loggedPreston-tube pressure differences (ie pp minus pinfin) must first be converted to a ∆p = pp minus ps

UNCLASSIFIED 13

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

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Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

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IFIE

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UN

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ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

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Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

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IFIE

D

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ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

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Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

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UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 2: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

Published by

DSTO Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

Telephone (03) 9626 7000Facsimile (03) 9626 7999

ccopy Commonwealth of Australia 2013AR No AR 015-744October 2013

APPROVED FOR PUBLIC RELEASE

ii UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Skin-Friction Measurements on a Model Submarine

Executive Summary

A series of experiments have been conducted in the Low-Speed Wind Tunnel at DSTO us-ing a generic submarine model (135 m long) to investigate the effect of different boundary-layer tripping devices1 on the skin-friction and pressure coefficients on the model Theresults also provide a reference data set to assist in the development and validation ofcomputational-fluid-dynamics codes

The submarine model tested was in a ldquobare-hullrdquo configuration aligned with the flowdirection The skin-friction was measured using a fine Pitot tube placed on the surface ofthe hull A Pitot tube used in this way is referred to as a Preston tube and the techniqueis applicable in regions where the boundary layer is in a turbulent state For regionswhere the boundary layer is laminar the Preston tube does not give quantitatively correctskin-friction values However the Preston tube was found to provide a useful means ofdetermining the location of the laminar to turbulent transition point

The results show the importance of correctly tripping the boundary layer and providea guide for selecting the size and type of tripping device required to achieve a correctly-stimulated turbulent boundary layer for a given wind tunnel velocity Only a limitedrange of trip sizes and types were tested but it was found that a trip wire of diameter02 mm or grit of size 80 give a correctly stimulated boundary layer However of these twodevices the wire is the preferred option since it was observed that grit may erode duringa testing program It is recommended that further work be carried out to quantify theskin friction in the laminar flow regions and the analysis be extended to other trip typessuch as cylindrical pins

The location of the tripping device was fixed relative to the model and this report doesnot address the difficult problem of where to place the trip

1A tripping device is used to force the boundary layer to transition from a laminar to turbulent state

UNCLASSIFIED iii

DSTOndashTRndash2898 UNCLASSIFIED

THIS PAGE IS INTENTIONALLY BLANK

iv UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Authors

Malcolm JonesAerospace Division

Malcolm Jones obtained a Bachelor of Engineering (Mechani-cal) degree in 1994 and a PhD in 1998 both from The Uni-versity of Melbourne His PhD involved an experimental andtheoretical study of a turbulent boundary layer developing in anaccelerated flow He joined the Defence Science and TechnologyOrganisation in 2007 where he is currently employed as a Re-search Scientist in Aerospace Division While at DSTO he hasbeen involved in aerodynamic testing of aircraft models such asthe F-35 and AP-3C in the Low Speed Wind Tunnel aeroacous-tic measurements and analysis of cavity flows and aerodynamicand structural measurements of flapping wings Prior to joiningDSTO he was employed as Research Fellow and then lecturerin the Department of Mechanical Engineering at The Univer-sity of Melbourne (1999-2003) From 2004-2007 he worked atthe School of Mathematical Sciences Queensland University ofTechnology During his academic appointments he gave lec-ture courses in fluid mechanics heat transfer manufacturingand mathematics and undertook research in turbulent bound-ary layer flows and biological fluid mechanics

UNCLASSIFIED v

DSTOndashTRndash2898 UNCLASSIFIED

Lincoln ErmAerospace Division

Lincoln Erm obtained a Bachelor of Engineering (Mechanical)degree in 1967 and a Master of Engineering Science degree in1969 both from the University of Melbourne His Masterrsquos de-gree was concerned with the yielding of aluminium alloy whensubjected to both tensile and torsional loading He joined theAeronautical Research Laboratories (now called the DefenceScience and Technology Organisation) in 1970 and has workedon a wide range of research projects including the prediction ofthe performance of gas-turbine engines under conditions of pul-sating flow parametric studies of ramrocket performance flowinstability in aircraft intakes and problems associated with thelanding of a helicopter on the flight deck of a ship Concurrentlywith some of the above work he studied at the University ofMelbourne and in 1988 obtained his Doctor of Philosophy de-gree for work on low-Reynolds-number turbulent boundary lay-ers Since this time he has undertaken research investigationsin the low-speed wind tunnel and the water tunnel Recentwork has been concerned with extending the testing capabili-ties of the water tunnel including developing a two-componentstrain-gauge-balance load-measurement system for the tunneland developing a dynamic-testing capability for the tunnel en-abling aerodynamic derivatives to be measured on models

Aliya ValiyffAerospace Division

Aliya Valiyff graduated from the University of Adelaide in 2009with a Bachelor of Aerospace Engineering and Bachelor of Sci-ence (Applied Mathematics and Physics) with 1st class honoursShe commenced work with DSTO in 2010 and during her timeshe has mainly worked within the Unmanned Aerial System -Corporate Enabling Research Programme (CERP) undertak-ing research on flapping wing and the flight and the UnderseaWarfare- CERP

vi UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Simon HenbestAerospace Division

Simon Henbest obtained a Bachelor of Engineering (Mechan-ical) degree with honours in 1977 and a PhD in 1983 bothfrom The University of Melbourne His PhD titled rdquoThe Struc-ture of Turbulent Pipe Flowrdquo provide experimental support toTownsendrsquos attached eddy hypothesis for wall bounded flowsIn 1984 he was awarded an Australian National Research Fel-lowship and continued wall turbulence research at the Univer-sity of Melbourne In 1987 he commenced employment at theAeronautical Research Laboratories (now called the DefenceScience and Technology Organisation) and obtained merit pro-motions to both Senior Research Scientist and Principal Re-search Scientist While at DSTO he has been involved in re-search into high speed jet and aeroacoustic cavity flows the IRsignature prediction of aircraft numerous aerodynamic testingprogrammes He has acted as a Research Leader for extendedperiods in AVD AOD and HPPD He is currently Head of FluidMechanics in Aerospace Division

UNCLASSIFIED vii

DSTOndashTRndash2898 UNCLASSIFIED

THIS PAGE IS INTENTIONALLY BLANK

viii UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Contents

Glossary xi

Notation xi

1 Introduction 1

11 Boundary-Layer Transition 1

12 Approach of Erm amp Joubert (1991) 2

13 Empirical Expressions to Determine Sizes of Tripping Devices 4

2 Preston-Tube Method of Measuring Skin-Friction Coefficients 4

3 Test Program 7

31 Test Facility 7

32 Test Model 7

33 Tripping Devices 10

34 Pressure Scanners 10

35 Data Acquisition Software 12

36 Experimental Procedure 12

37 Data Reduction 13

4 Results 14

41 Skin Friction Without a Tripping Device 14

42 Skin Friction With Tripping Devices 16

421 Comparison of the Different Trip Devices 21

422 Scaling of Skin Friction with Reynolds Number 22

423 Over-stimulation and the Maximum Trip Reynolds Number 23

43 Pressure Coefficients 24

44 Pressure Gradients 26

5 Comparison with CFD Predictions 29

6 Conclusions 30

7 Acknowledgements 32

Appendices

UNCLASSIFIED ix

DSTOndashTRndash2898 UNCLASSIFIED

A Summary of Tripping Devices Used in Previous Experiments 35

B Preston Tube Data Processing 36

C Skin Friction Coefficients 37

D Pressure Coefficients 45

x UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Glossary

DARPA Defense Advanced Research Projects AgencyCERP Corporate Enabling Research ProgramCFD Computational Fluid DynamicsLSWT Low-Speed Wind TunnelDSTO Defence Science and Technology Organisation

Notation

Cf Local skin-friction coefficientCp Pressure coefficientd Outer diameter of Preston tubedT Diameter of trip wireh Height of grit transition strippinfin Free-stream static pressurepp Total pressure of Preston tubeps Model surface static pressurept Free-stream total pressurep+x Non-dimensional pressure gradient parameterRe Reynolds numberRedT Reynolds number based on diameter of wireRex Reynolds number based on the stream-wise coordinateRext Streamwise Reynolds number of transition pointU Streamwise velocity in boundary layerU1 Streamwise velocity at edge of boundary layerUinfin Nominal streamwise velocity in tunnel working-sectionUτ Friction velocityw Width of grit transition stripx Streamwise coordinatext Streamwise coordinate of transition pointy Wall normal coordinate∆p ∆p = pp minus psν Kinematic viscosityρ Fluid densityτ0 Wall shear stress

UNCLASSIFIED xi

DSTOndashTRndash2898 UNCLASSIFIED

THIS PAGE IS INTENTIONALLY BLANK

xii UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

1 Introduction

This work aims to understand flow fields about a submarine As part of this programa series of experiments have been conducted in the Low-Speed Wind Tunnel (LSWT) atthe Defence Science and Technology Organisation (DSTO) to quantify the skin-frictiondistributions on a generic submarine model and in the process investigate the effectivenessof a limited range of tripping devices The results also provide a reference data set forcomputational fluid dynamics (CFD) validation of a submarine model

When conducting tests in wind tunnels on a sub-scale model for results of the exper-iment to be transferable to the full-scale vehicle the flow patterns and load coefficientson the model and the full-size vehicle need to be made similar Ideally this is achievedthrough matching the Reynolds number of the flow over the model to that of the full-scalevehicle However in practice this is difficult to achieve and is not always possible To en-sure that the flow features on the model are representative of those for the full-size vehiclea tripping device can be used such that the boundary layers (ie regions of laminar flowlaminar-to-turbulent transition and turbulent flow) are made similar However differenttripping devices can impart different disturbances into the flow In order to correctly stim-ulate the boundary layer on the submarine model and avoid over- or under-stimulationthe type and size of tripping devices need to be selected for a given Reynolds numberor Reynolds number range and also for a specific trip location Additionally the chosentripping device will be specific to a given tunnel and would be dependent on factors suchas the level of free-stream turbulence in the tunnel

dT

Ud

Trip wire

xd

Laminar Transition Turbulent

Boundary-layeredge

U1

Figure 1 Diagrammatic representation of a boundary layer being tripped based on adiagram given by White (1974)

11 Boundary-Layer Transition

Boundary-layer transition is a complicated physical process dependent on instability mech-anisms including Tollmien-Schlichting waves crossflow and Gortler instabilities (see Reedamp Saric 2008) Over the years there have been numerous articles published on transi-tion both from experimental investigations and CFD analyses in low-speed transonic

UNCLASSIFIED 1

DSTOndashTRndash2898 UNCLASSIFIED

and hypersonic flow regimes (for example Schlatter amp Henningson 2009) Details of thetransition process are still not fully understood In the present report transition physicalprocesses are not considered instead attention is focused on how to stabilise the posi-tion of the transition using a tripping device and to ensure that the turbulent boundarylayer is neither under- or over-stimulated irrespective of the flow physics associated withtransition

12 Approach of Erm amp Joubert (1991)

A diagrammatic representation of a boundary layer being tripped is shown in Figure 1where dT is the height of the tripping device U1 is the streamwise velocity at the edge ofthe boundary layer xd is the location of the tripping device measured from the nose ofthe model and Ud is the velocity in the boundary layer at the top of the device

A question that had to be addressed was what is the best size and type of trippingdevice to use in the current experiments in the LSWT to trip the boundary layer on thesubmarine model Erm amp Joubert (1991) faced a similar question in their studies on low-Reynolds-number flows over a smooth flat surface in a zero pressure gradient For differenttypes of tripping devices they measured longitudinal skin-friction coefficients for a rangeof free-stream velocities Their data for a 12 mm wire tripping device are reproduced inFigure 2 From this figure it can be seen that as the velocity is increased from 8 ms thedevice imparts an increased amount of turbulent energy into the flow so that the laminar-to-turbulent transition region moves upstream They conjectured that correct stimulationis associated with a particular curve when the peaks of successive curves correspondingto higher velocities do not advance significantly upstream Velocities lower than thatcorresponding to the particular curve were obviously associated with under-stimulatedflows since the peaks of the curves were well downstream of the device and thus thedevice was therefore not completely effective in tripping the flow Since the velocitycorresponding to the particular curve establishes a turbulent boundary layer almost to thepossible upstream limit of turbulent flow it seemed reasonable to assume that the maineffect of higher velocities was to overstimulate the flow

The x-coordinate corresponding to the peaks of Figure 2 are plotted in Figure 3 as afunction of streamwise velocity and it is apparent that the above condition for correct stim-ulation was satisfied when the velocity was between 10 and 12 ms This corresponds to aminimum Reynolds number of the tripping device in the range of RedT = U1dT ν = 800to 960 where ν is the kinematic viscosity For the case where a trip device has aReynolds number greater than the minimum required the tripping device may overstim-ulate the flow Note over-stimulation does not necessarily result in higher skin-frictionwhen compared to a correctly stimulated layer Rather it means that the disturbanceintroduced by the tripping device is felt downstream of the transition region and leadsto a ldquonon-standardrdquo turbulent boundary initially developing Ideally to assess whetherover-stimulation has occurred complete velocity profiles in the turbulent region need tobe measured and compared against reference data sets such as those collated by Coles(1962)

It should be noted that in the current work the boundary layer develops in a pressuregradient with wall curvature in both the streamwise and spanwise directions Whereas

2 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

the work of Erm amp Joubert (1991) was undertaken on a flat plate zero pressure gradientthis means the RedT values given above cannot be applied directly to predict the trip sizerequired However the approach taken here broadly follows that of Erm amp Joubert (1991)in that a range of trip Reynolds numbers were tested (by varying both freestream velocityand trip size) and the skin-friction downstream of the trip measured

0 01 02x (m)

03 04 05

Figure 2 Cf vs x measurements for a 12 mm diameter trip wire for different free-streamvelocities as obtained by Erm amp Joubert (1991)

8 9 10 11 12 13 14

xlocation

(m)of

peakCf

Location of peak Cf

Location of trip device

01

02

0

Uinfin (ms)

Figure 3 Location of the peak Cf values shown in Figure 2

UNCLASSIFIED 3

DSTOndashTRndash2898 UNCLASSIFIED

13 Empirical Expressions to Determine Sizes of TrippingDevices

Researchers have proposed different empirical expressions for determining the size of deviceto use to trip the flow The relationships incorporate parameters including the height ofthe tripping device dT the velocity at the edge of the boundary layer U1 the velocity inthe undisturbed boundary layer at the top of the device Ud and the wall friction velocityevaluated at the device Uτ The friction velocity is defined by τ0 = ρU2

τ where τ0 is thesurface shear stress and ρ is the fluid density Recommendations for fully-effective trippingcover quite a wide range Tani et al (1940) proposed the criterion UτdT ν = 13 Fage ampPreston (1941) proposed UτdT ν = 20 Braslow amp Knox (1958) proposed UddT ν = 600and Gibbings (1959) proposed U1dT ν = 826 It should be noted that the criterion ofGibbings (1959) is based on a review of many data sets included those of Tani amp Sato(1956) and Fage amp Preston (1941) Gibbings (1959) expresses the Tani amp Sato (1956)and Fage amp Preston (1941) criteria as Reynolds numbers based on the freestream velocitywhich gives values of U1dT ν = 600 and 840 respectively The criterion given aboverepresent minimum values of the tripping device Reynolds number required to correctlytrip the boundary layer and agree with the results of Erm amp Joubert (1991)

An analysis of the literature for tests done on bodies of revolution indicated that thereis no consistent approach for selecting the size and type of device to use on such bodiesAppendix A gives details of devices used by different investigators for bodies of revolutiontogether with other experimental information Based on the freestream velocity and tripheight the Reynolds numbers of the trip devices given in Appendix A range from 200 to40 times 103 For the present investigation the approach used to establish the effects thatdifferent devices had on tripping laminar boundary layers was similar to that used byErm amp Joubert (1991) for a smooth flat plate in a zero pressure gradient Using theirtechnique it is possible to establish the size and type of tripping device to be used for agiven velocity to obtain correctly stimulated turbulent boundary layers

2 Preston-Tube Method of Measuring

Skin-Friction Coefficients

Skin-friction coefficients in a turbulent boundary layer flowing over a smooth surface canbe measured in a number of different ways (Fernholz et al 1996) including using Prestontubes (Preston 1954) from velocity profiles and using devices mounted flush with thesurface of a model Of the alternative approaches the Preston-tube method is convenientand is widely used The method makes use of a simple Pitot tube placed on the surfaceof a body and when used this way it is termed a Preston tube The method depends onan underlining assumption that in the region adjacent to the surface the flow is primarilydetermined by the surface shear stress and the properties of the fluid and is independentof factors such as pressure gradient and surface curvature The assumption implies thatthe velocity profile in a turbulent boundary layer adjacent to the surface is given by

U

Uτ= f

(Uτy

ν

)(1)

4 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

where U is the local stream-wise velocity Uτ is the friction velocity f is a universalfunction y is the wall normal coordinate and ν is the kinematic viscosity Equation (1) isoften referred to as the ldquolaw of the wallrdquo (Coles 1956)

A Pitot tube placed on the wall will measure a pressure relative to the wall staticpressure of ∆p = ρU22 at an effective coordinate y = c0d where d is the outer diameterof the Pitot tube and c0 is an unknown constant Substituting the values U =

radic(2∆pρ)

and y = cod into (1) yields a relationship between the wall shear stress fluid propertiesPreston-tube pressure difference and the tube diameter which is given by

2∆p

ρUτ2 =

[f

(Uτ c0d

ν

)]2 (2)

Alternatively for the purpose of measuring skin friction (2) can be expressed more con-veniently in the form

τ0d2

4ρν2= F

(∆pd2

4ρν2

)(3)

where c0 has been absorbed into the function F The function F represents the ldquocalibra-tionrdquo function for a Preston tube and several experimentally derived forms exist in theliterature (see Preston 1954 Patel 1965 Zagarola et al 2001) Generally the calibrationis determined by placing the Preston tube in a pipe flow where the wall shear stress (orfriction factor) can be determined accurately by measuring the pressure gradient in thepipe

For the data presented in this report the calibration of Patel (1965) was used todetermine the wall shear stress The calibration curve of Patel (1965) is given as follows

xlowast =ylowast + 2 log10(195ylowast + 410) for 55 ltUτd

2νlt 800 (4)

ylowast =08287 minus 01381xlowast + 01437xlowast2 minus 0006xlowast3 for 56 ltUτd

2νlt 55 and (5)

ylowast =1

2xlowast + 0037 for

Uτd

2νlt 56 (6)

where

xlowast = log10

(∆pd2

4ρν2

)and ylowast = log10

(τ0d

2

4ρν2

)

The local skin friction coefficient Cf is then found using

Cf =τ0

12ρU

21

(7)

where U1 is the streamwise velocity at the edge of the boundary layer

The calibration given by (4)-(6) is valid only for a hydrodynamically smooth surfaceA surface is considered hydrodynamically smooth provided that the height of surfaceroughness elements remain less than 5νUτ (Jimenez 2004) The minimum value of 5νUτthat was measured was approximately 4microm and the measured surface finish was found tobe an order of magnitude less than this value (Section 32) Hence the requirement of ahydrodynamically smooth surface is satisfied for this experiment

UNCLASSIFIED 5

DSTOndashTRndash2898 UNCLASSIFIED

The fundamental requirement for using a Preston tube is that the boundary layer isin a turbulent state and that the dimension of the Preston tube is such that it remainswithin the region where (1) is valid (ie from (4) Uτdν lt 1600) The diameter of thePreston tube for all experiments was d = 06 mm and this ensured that Uτdν remainedless than 1600 well within the range of the calibration (4)

It is known that for sufficiently strong pressure gradients the form of (1) changes (seeNickels 2004) Patel (1965) quantifies the effect of pressure gradients using the non-dimensional pressure gradient parameter1

p+x =ν

ρU3τ

dp

dx (8)

The error associated with using a Preston tube in pressure gradients is quantified by Patel(1965) and is given by the following inequalities

1 Adverse pressure gradient

Max Error 3 0 lt p+x lt 001 andUτd

νle 200 (9a)

Max Error 6 0 lt p+x lt 0015 andUτd

νle 250 (9b)

2 Favourable pressure gradient

Max Error 3 minus0005 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10a)

Max Error 6 minus0007 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10b)

The pressure gradient data are presented in Section 44 and were found to fall within thelimits of (9a) and (10a) indicating that the skin-friction coefficients are valid to withinplusmn3 This accuracy is similar to the alternative direct skin-friction measuring techniqueswhich typically achieve an accuracy of plusmn4 (Fernholz et al 1996)

The effect of model spanwise curvature on (4)-(6) is not quantified A reasonableassumption is that since the boundary layer thickness is much less than the model diameterthe effect of spanwise model curvature can be neglected

The Preston-tube method as outlined above requires that the boundary layer is in aturbulent state For this reason the method cannot be used to infer the skin friction atlocations were the boundary layer is in a laminar state However the ∆p values read by thePreston tube can be used to determine where laminar-to-turbulent transition occurs Theregion of transition is associated with a discontinuity in ∆p when plotted as a functionof streamwise coordinate x as shown by Erm amp Joubert (1991)

1for clarity we have adopted the notation for the pressure gradient parameter used by Nickels (2004)Patel (1965) uses the symbol ∆

6 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 4 LSWT Layout see Erm (2003)

3 Test Program

In this preliminary investigation four different tripping devices were used to investigatethe effect of the device on the skin-friction profile of a generic sub-scale submarine modelTests were conducted both with and without the tripping devices at a range of nominalfree-stream velocities Uinfin ranging from Uinfin = 40 to 70 ms to assess their effectivenessin tripping the boundary layer

31 Test Facility

The Low-Speed Wind Tunnel at DSTO is a closed circuit continuous flow tunnel with acontraction ratio of 41 The test section has an irregular octagonal shape with a heightof 213 m a width of 274 m and a length of 6553 m with a longitudinal turbulenceintensity of approximately 04 in the region where the models are tested (see Erm2003) An outline of the plan of the wind tunnel is shown in Figure 4 Free-streamvelocities were measured using static pressure rings at the upstream and downstreamends of the contraction A Pitot-static probe mounted on the side wall near the front ofthe working section was used to provide an independent measurement of the free-streamvelocity

32 Test Model

The sub-scale submarine model utilised in these tests is referred to as the Joubert modelsince the geometry is based on the work of Joubert (2004) and Joubert (2006) as well asLoid amp Bystrom (1983) The model was designed for the purpose of experimental and

UNCLASSIFIED 7

DSTOndashTRndash2898 UNCLASSIFIED

1

2 345

6 7 8 91011

12 13 141516

17 181920

212223

24 252627

28 29 303132

33 34

35

Top view

Side view

Figure 5 Schematic of scale model showing static-pressure port locations green and redmarkers represent the starboard and port static-pressure ports respectively

numerical studies and has no full-scale equivalent While the full model includes a casingcentre fin and control surfaces all tests reported here were conducted on the axisymmetricbody shape only

The model was machined from aluminum and consists of an ellipsoidal nose a cylin-drical centre-body and a streamlined tail section At the design stage an N6 surface finishwas specified for the model which corresponds to a roughness of 08microm in waviness Af-ter manufacture the surface finish was checked using a Surface Roughness Indicator andthe finish was found to be better than the design specification The model was anodisedwhich increased the thickness of the natural oxide layer by about 10microm

The model is 1350 mm long with a maximum diameter of 185 mm and slendernessratio of 73 where the slenderness ratio is defined as hull length divided by maximumhull diameter The model contains 21 longitudinal static-pressure ports on the centre-lineof the upper surface and 14 lateral static-pressure ports offset to the port and starboardsides of the upper surface centre-line Figure 5 shows the stream-wise location of thestatic-pressure ports

The model was supported by a single pylon as shown in Figure 6 All tests were carriedout at zero angle of yaw and zero angle of pitch The origin of the body coordinate systemis located at the nose of the submarine model The x-axis corresponds to the axis ofsymmetry of the model

8 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 6 Submarine model mounted in LSWT showing pylon support and pitch controlarm

UNCLASSIFIED 9

DSTOndashTRndash2898 UNCLASSIFIED

Table 1 Details of tripping devices where the Reynolds number is based on the height ofthe device The minimum Reynolds number and maximum Reynolds number correspondto nominal freestream velocities of Uinfin = 40 ms and Uinfin = 70 ms respectively where his the height of the grit and w is the width of the grit

Device Dimensions (mm) RedT (min) RedT (max)

Wire 1 dT = 01 281 496Wire 2 dT = 02 577 1015Wire 3 dT = 05 1443 256680 Grit h = 021 w = 3 605 1073

33 Tripping Devices

In this work four tripping devices were tested and consisted of circular wires with diame-ters dT = 01 02 and 05 mm as well as a distributed silicon carbide grit of size 80 havinga width of 3 mm The circular wires were bent to conform to the local diameter of thesubmarine and then attached with ldquosuper-gluerdquo such that there was no gap between thewire and the model surface Figure 7 The silicon carbide grit is prepared by distributinga layer of grit on double-sided sticky tape the tape is then adhered to the submarineFigure 8 The tripping devices were attached to the submarine model circumferentiallylocated at a streamwise coordinate of x = 675 mm measured from the nose of the sub-marine which corresponds to 5 of the total model length The dimensions of the tripdevices along with the Reynolds number range of the trip devices are summarised inTable 1 Note that the Reynolds number of the trip device is defined as RedT = U1dT νwhere for the case of the 80 grit dT is replaced by the grit height h

34 Pressure Scanners

Pressure Systems Incorporated (PSI) brand pressure scanners were used to measure allstatic and total pressures The pressure scanners are differential pressure measurementunits consisting of an array of silicon piezoresistive pressure sensors one for each pressureport The outputs of the sensors are electronically multiplexed through a single on-boardinstrumentation amplifier using binary addressing The scanners include a two-positioncalibration manifold actuated by momentary pulses of control pressures In the calibrateposition all sensors are connected to a common calibration pressure port A series ofaccurately-measured pressures is applied through this port to characterize the sensorsProper and periodic on-line calibration maintains static errors within plusmn003 or betterof the full-scale pressure range

The pressure scanners are controlled and sampled using a PSI 8400 electronic measure-ment system It is a modular parallel processing system for high-speed pressure scanningat up to 20000 measurements per second and allows the use of digitally temperaturecompensated pressure scanners

Two differential pressure scanners were used in the experiments All pressures aremeasured relative to the free-stream static pressure pinfin as measured by the referencefree-stream Pitot-static probe Each pressure scanner contained 32 ports The full-scale

10 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 7 Location of trip wire

Figure 8 Photo showing the 3 mm wide band of 80 grit transition strip

UNCLASSIFIED 11

DSTOndashTRndash2898 UNCLASSIFIED

pressure range of the scanners is 249 kPa (ldquo10 inches-of-water scannerrdquo) and 689 kPa(ldquo1 psi scannerrdquo) The 689 kPa scanner was used to read the static pressure at the longi-tudinal ports as well as the output from the Preston tube and the Pitot-static probe

For the purpose of cross-checking and for redundancy the Preston tube was connectedto two independent ports of the 689 kPa scanner and the two readings averaged For thisscanner pressures could be read to an accuracy of 6890 times 00003 Pa ie about 2 Pa Theminimum ∆p measured by the Preston tube was 145 Pa which gives a pressure scannerresolution of 14 However this minimum ∆p was recorded for a location where thePreston tube was in a laminar boundary layer and such data is only useful in a qualitativesense (see Section 2) For locations were the boundary layer is turbulent the minimum ∆pwas 340 Pa which gives a pressure scanner resolution of 06 The 249 kPa scanner wasused mainly to acquire the static pressures at the lateral ports

35 Data Acquisition Software

A software package called ImPressOne was used which communicates with the PSI 8400and displays and acquires the pressure data for the model under test For the staticpressure measurements 100 readings were acquired at each pressure port at a samplingrate of 20 Hz For the Preston-tube measurements the sample rate was increased and100 samples were acquired at each pressure port at a sampling rate of 50 Hz for eachfree-stream velocity

36 Experimental Procedure

The hull was tested with each of the selected tripping devices listed in Table 1 as wellas without a tripping device resulting in five different test configurations For each testconfiguration the static pressures were initially acquired for that particular configurationfollowed by the Preston-tube measurements

A Preston tube having a diameter of 06 mm was attached to the surface of the modelusing both plasticine and tape to ensure that the tube was positioned as flat as possibleon the surface of the model as shown in Figure 9 Preston-tube measurement were takenon the upper surface of the submarine model along a line directly above the centre-lineof the model For the dT = 02 and 05 mm wires and the grit case measurements weretaken from x = 73 mm to x = 1065 mm for a total of 18 stations For the dT = 01 mmwire measurements were limited to 3 stations between x = 305 mm and x = 442 mmThe stream-wise coordinates for the Preston tube measurements are given in the Table 2Data were acquired for a range of free-stream velocities from 40 to 70 ms in incrementsof 5 ms

For each nominal velocity the corresponding model Reynolds number was calcu-lated assuming standard temperature and atmospheric pressure conditions 20C and101 325 Pa respectively For each given test the temperature and static pressure of theair within the test section were logged and the air density and viscosity were calculatedTo account for daily variations in temperature and atmospheric pressure the freestream

12 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Flow direction

Figure 9 Preston tube located on the centre-line of the upper-surface of submarine

velocity was adjusted to ensure that the model Reynolds number remained constant foreach given nominal velocity condition as shown in Table 3

Table 2 Skin-friction measurement stations Where applicable the corresponding staticport number is given For the dT = 01 mm wire measurements were only taken at stations3050 3600 as well as an additional station at x = 4425 mm

xmm 731 787 843 900 1125 1350 1575 1800 2150Static port - - - 6 - 7 - 8 -

xmm 2500 3050 3600 5250 7000 8700 9500 10100 10650Static port 9 - 12 13 14 17 18 21 24

Table 3 Reynolds numbers (based on submarine length 135 m) corresponding to thenominal free-stream velocities

Nominal Uinfin 40 45 50 55 60 65 70 msRe 358 403 448 493 537 582 627 times106

37 Data Reduction

The static pressure readings from the pressure ports were converted to pressure coefficientsusing the relationship

Cp =ps minus pinfinpt minus pinfin

(11)

where pinfin is the reference free-stream static pressure pt is the reference free-stream totalpressure and ps is the static pressure on the surface of the submarine model

As explained in Section 34 all Preston tube pressures are measured relative to the free-stream static pressure In order to apply the Preston tube calibration (4)-(6) the loggedPreston-tube pressure differences (ie pp minus pinfin) must first be converted to a ∆p = pp minus ps

UNCLASSIFIED 13

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

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IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 3: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

Skin-Friction Measurements on a Model Submarine

Executive Summary

A series of experiments have been conducted in the Low-Speed Wind Tunnel at DSTO us-ing a generic submarine model (135 m long) to investigate the effect of different boundary-layer tripping devices1 on the skin-friction and pressure coefficients on the model Theresults also provide a reference data set to assist in the development and validation ofcomputational-fluid-dynamics codes

The submarine model tested was in a ldquobare-hullrdquo configuration aligned with the flowdirection The skin-friction was measured using a fine Pitot tube placed on the surface ofthe hull A Pitot tube used in this way is referred to as a Preston tube and the techniqueis applicable in regions where the boundary layer is in a turbulent state For regionswhere the boundary layer is laminar the Preston tube does not give quantitatively correctskin-friction values However the Preston tube was found to provide a useful means ofdetermining the location of the laminar to turbulent transition point

The results show the importance of correctly tripping the boundary layer and providea guide for selecting the size and type of tripping device required to achieve a correctly-stimulated turbulent boundary layer for a given wind tunnel velocity Only a limitedrange of trip sizes and types were tested but it was found that a trip wire of diameter02 mm or grit of size 80 give a correctly stimulated boundary layer However of these twodevices the wire is the preferred option since it was observed that grit may erode duringa testing program It is recommended that further work be carried out to quantify theskin friction in the laminar flow regions and the analysis be extended to other trip typessuch as cylindrical pins

The location of the tripping device was fixed relative to the model and this report doesnot address the difficult problem of where to place the trip

1A tripping device is used to force the boundary layer to transition from a laminar to turbulent state

UNCLASSIFIED iii

DSTOndashTRndash2898 UNCLASSIFIED

THIS PAGE IS INTENTIONALLY BLANK

iv UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Authors

Malcolm JonesAerospace Division

Malcolm Jones obtained a Bachelor of Engineering (Mechani-cal) degree in 1994 and a PhD in 1998 both from The Uni-versity of Melbourne His PhD involved an experimental andtheoretical study of a turbulent boundary layer developing in anaccelerated flow He joined the Defence Science and TechnologyOrganisation in 2007 where he is currently employed as a Re-search Scientist in Aerospace Division While at DSTO he hasbeen involved in aerodynamic testing of aircraft models such asthe F-35 and AP-3C in the Low Speed Wind Tunnel aeroacous-tic measurements and analysis of cavity flows and aerodynamicand structural measurements of flapping wings Prior to joiningDSTO he was employed as Research Fellow and then lecturerin the Department of Mechanical Engineering at The Univer-sity of Melbourne (1999-2003) From 2004-2007 he worked atthe School of Mathematical Sciences Queensland University ofTechnology During his academic appointments he gave lec-ture courses in fluid mechanics heat transfer manufacturingand mathematics and undertook research in turbulent bound-ary layer flows and biological fluid mechanics

UNCLASSIFIED v

DSTOndashTRndash2898 UNCLASSIFIED

Lincoln ErmAerospace Division

Lincoln Erm obtained a Bachelor of Engineering (Mechanical)degree in 1967 and a Master of Engineering Science degree in1969 both from the University of Melbourne His Masterrsquos de-gree was concerned with the yielding of aluminium alloy whensubjected to both tensile and torsional loading He joined theAeronautical Research Laboratories (now called the DefenceScience and Technology Organisation) in 1970 and has workedon a wide range of research projects including the prediction ofthe performance of gas-turbine engines under conditions of pul-sating flow parametric studies of ramrocket performance flowinstability in aircraft intakes and problems associated with thelanding of a helicopter on the flight deck of a ship Concurrentlywith some of the above work he studied at the University ofMelbourne and in 1988 obtained his Doctor of Philosophy de-gree for work on low-Reynolds-number turbulent boundary lay-ers Since this time he has undertaken research investigationsin the low-speed wind tunnel and the water tunnel Recentwork has been concerned with extending the testing capabili-ties of the water tunnel including developing a two-componentstrain-gauge-balance load-measurement system for the tunneland developing a dynamic-testing capability for the tunnel en-abling aerodynamic derivatives to be measured on models

Aliya ValiyffAerospace Division

Aliya Valiyff graduated from the University of Adelaide in 2009with a Bachelor of Aerospace Engineering and Bachelor of Sci-ence (Applied Mathematics and Physics) with 1st class honoursShe commenced work with DSTO in 2010 and during her timeshe has mainly worked within the Unmanned Aerial System -Corporate Enabling Research Programme (CERP) undertak-ing research on flapping wing and the flight and the UnderseaWarfare- CERP

vi UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Simon HenbestAerospace Division

Simon Henbest obtained a Bachelor of Engineering (Mechan-ical) degree with honours in 1977 and a PhD in 1983 bothfrom The University of Melbourne His PhD titled rdquoThe Struc-ture of Turbulent Pipe Flowrdquo provide experimental support toTownsendrsquos attached eddy hypothesis for wall bounded flowsIn 1984 he was awarded an Australian National Research Fel-lowship and continued wall turbulence research at the Univer-sity of Melbourne In 1987 he commenced employment at theAeronautical Research Laboratories (now called the DefenceScience and Technology Organisation) and obtained merit pro-motions to both Senior Research Scientist and Principal Re-search Scientist While at DSTO he has been involved in re-search into high speed jet and aeroacoustic cavity flows the IRsignature prediction of aircraft numerous aerodynamic testingprogrammes He has acted as a Research Leader for extendedperiods in AVD AOD and HPPD He is currently Head of FluidMechanics in Aerospace Division

UNCLASSIFIED vii

DSTOndashTRndash2898 UNCLASSIFIED

THIS PAGE IS INTENTIONALLY BLANK

viii UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Contents

Glossary xi

Notation xi

1 Introduction 1

11 Boundary-Layer Transition 1

12 Approach of Erm amp Joubert (1991) 2

13 Empirical Expressions to Determine Sizes of Tripping Devices 4

2 Preston-Tube Method of Measuring Skin-Friction Coefficients 4

3 Test Program 7

31 Test Facility 7

32 Test Model 7

33 Tripping Devices 10

34 Pressure Scanners 10

35 Data Acquisition Software 12

36 Experimental Procedure 12

37 Data Reduction 13

4 Results 14

41 Skin Friction Without a Tripping Device 14

42 Skin Friction With Tripping Devices 16

421 Comparison of the Different Trip Devices 21

422 Scaling of Skin Friction with Reynolds Number 22

423 Over-stimulation and the Maximum Trip Reynolds Number 23

43 Pressure Coefficients 24

44 Pressure Gradients 26

5 Comparison with CFD Predictions 29

6 Conclusions 30

7 Acknowledgements 32

Appendices

UNCLASSIFIED ix

DSTOndashTRndash2898 UNCLASSIFIED

A Summary of Tripping Devices Used in Previous Experiments 35

B Preston Tube Data Processing 36

C Skin Friction Coefficients 37

D Pressure Coefficients 45

x UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Glossary

DARPA Defense Advanced Research Projects AgencyCERP Corporate Enabling Research ProgramCFD Computational Fluid DynamicsLSWT Low-Speed Wind TunnelDSTO Defence Science and Technology Organisation

Notation

Cf Local skin-friction coefficientCp Pressure coefficientd Outer diameter of Preston tubedT Diameter of trip wireh Height of grit transition strippinfin Free-stream static pressurepp Total pressure of Preston tubeps Model surface static pressurept Free-stream total pressurep+x Non-dimensional pressure gradient parameterRe Reynolds numberRedT Reynolds number based on diameter of wireRex Reynolds number based on the stream-wise coordinateRext Streamwise Reynolds number of transition pointU Streamwise velocity in boundary layerU1 Streamwise velocity at edge of boundary layerUinfin Nominal streamwise velocity in tunnel working-sectionUτ Friction velocityw Width of grit transition stripx Streamwise coordinatext Streamwise coordinate of transition pointy Wall normal coordinate∆p ∆p = pp minus psν Kinematic viscosityρ Fluid densityτ0 Wall shear stress

UNCLASSIFIED xi

DSTOndashTRndash2898 UNCLASSIFIED

THIS PAGE IS INTENTIONALLY BLANK

xii UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

1 Introduction

This work aims to understand flow fields about a submarine As part of this programa series of experiments have been conducted in the Low-Speed Wind Tunnel (LSWT) atthe Defence Science and Technology Organisation (DSTO) to quantify the skin-frictiondistributions on a generic submarine model and in the process investigate the effectivenessof a limited range of tripping devices The results also provide a reference data set forcomputational fluid dynamics (CFD) validation of a submarine model

When conducting tests in wind tunnels on a sub-scale model for results of the exper-iment to be transferable to the full-scale vehicle the flow patterns and load coefficientson the model and the full-size vehicle need to be made similar Ideally this is achievedthrough matching the Reynolds number of the flow over the model to that of the full-scalevehicle However in practice this is difficult to achieve and is not always possible To en-sure that the flow features on the model are representative of those for the full-size vehiclea tripping device can be used such that the boundary layers (ie regions of laminar flowlaminar-to-turbulent transition and turbulent flow) are made similar However differenttripping devices can impart different disturbances into the flow In order to correctly stim-ulate the boundary layer on the submarine model and avoid over- or under-stimulationthe type and size of tripping devices need to be selected for a given Reynolds numberor Reynolds number range and also for a specific trip location Additionally the chosentripping device will be specific to a given tunnel and would be dependent on factors suchas the level of free-stream turbulence in the tunnel

dT

Ud

Trip wire

xd

Laminar Transition Turbulent

Boundary-layeredge

U1

Figure 1 Diagrammatic representation of a boundary layer being tripped based on adiagram given by White (1974)

11 Boundary-Layer Transition

Boundary-layer transition is a complicated physical process dependent on instability mech-anisms including Tollmien-Schlichting waves crossflow and Gortler instabilities (see Reedamp Saric 2008) Over the years there have been numerous articles published on transi-tion both from experimental investigations and CFD analyses in low-speed transonic

UNCLASSIFIED 1

DSTOndashTRndash2898 UNCLASSIFIED

and hypersonic flow regimes (for example Schlatter amp Henningson 2009) Details of thetransition process are still not fully understood In the present report transition physicalprocesses are not considered instead attention is focused on how to stabilise the posi-tion of the transition using a tripping device and to ensure that the turbulent boundarylayer is neither under- or over-stimulated irrespective of the flow physics associated withtransition

12 Approach of Erm amp Joubert (1991)

A diagrammatic representation of a boundary layer being tripped is shown in Figure 1where dT is the height of the tripping device U1 is the streamwise velocity at the edge ofthe boundary layer xd is the location of the tripping device measured from the nose ofthe model and Ud is the velocity in the boundary layer at the top of the device

A question that had to be addressed was what is the best size and type of trippingdevice to use in the current experiments in the LSWT to trip the boundary layer on thesubmarine model Erm amp Joubert (1991) faced a similar question in their studies on low-Reynolds-number flows over a smooth flat surface in a zero pressure gradient For differenttypes of tripping devices they measured longitudinal skin-friction coefficients for a rangeof free-stream velocities Their data for a 12 mm wire tripping device are reproduced inFigure 2 From this figure it can be seen that as the velocity is increased from 8 ms thedevice imparts an increased amount of turbulent energy into the flow so that the laminar-to-turbulent transition region moves upstream They conjectured that correct stimulationis associated with a particular curve when the peaks of successive curves correspondingto higher velocities do not advance significantly upstream Velocities lower than thatcorresponding to the particular curve were obviously associated with under-stimulatedflows since the peaks of the curves were well downstream of the device and thus thedevice was therefore not completely effective in tripping the flow Since the velocitycorresponding to the particular curve establishes a turbulent boundary layer almost to thepossible upstream limit of turbulent flow it seemed reasonable to assume that the maineffect of higher velocities was to overstimulate the flow

The x-coordinate corresponding to the peaks of Figure 2 are plotted in Figure 3 as afunction of streamwise velocity and it is apparent that the above condition for correct stim-ulation was satisfied when the velocity was between 10 and 12 ms This corresponds to aminimum Reynolds number of the tripping device in the range of RedT = U1dT ν = 800to 960 where ν is the kinematic viscosity For the case where a trip device has aReynolds number greater than the minimum required the tripping device may overstim-ulate the flow Note over-stimulation does not necessarily result in higher skin-frictionwhen compared to a correctly stimulated layer Rather it means that the disturbanceintroduced by the tripping device is felt downstream of the transition region and leadsto a ldquonon-standardrdquo turbulent boundary initially developing Ideally to assess whetherover-stimulation has occurred complete velocity profiles in the turbulent region need tobe measured and compared against reference data sets such as those collated by Coles(1962)

It should be noted that in the current work the boundary layer develops in a pressuregradient with wall curvature in both the streamwise and spanwise directions Whereas

2 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

the work of Erm amp Joubert (1991) was undertaken on a flat plate zero pressure gradientthis means the RedT values given above cannot be applied directly to predict the trip sizerequired However the approach taken here broadly follows that of Erm amp Joubert (1991)in that a range of trip Reynolds numbers were tested (by varying both freestream velocityand trip size) and the skin-friction downstream of the trip measured

0 01 02x (m)

03 04 05

Figure 2 Cf vs x measurements for a 12 mm diameter trip wire for different free-streamvelocities as obtained by Erm amp Joubert (1991)

8 9 10 11 12 13 14

xlocation

(m)of

peakCf

Location of peak Cf

Location of trip device

01

02

0

Uinfin (ms)

Figure 3 Location of the peak Cf values shown in Figure 2

UNCLASSIFIED 3

DSTOndashTRndash2898 UNCLASSIFIED

13 Empirical Expressions to Determine Sizes of TrippingDevices

Researchers have proposed different empirical expressions for determining the size of deviceto use to trip the flow The relationships incorporate parameters including the height ofthe tripping device dT the velocity at the edge of the boundary layer U1 the velocity inthe undisturbed boundary layer at the top of the device Ud and the wall friction velocityevaluated at the device Uτ The friction velocity is defined by τ0 = ρU2

τ where τ0 is thesurface shear stress and ρ is the fluid density Recommendations for fully-effective trippingcover quite a wide range Tani et al (1940) proposed the criterion UτdT ν = 13 Fage ampPreston (1941) proposed UτdT ν = 20 Braslow amp Knox (1958) proposed UddT ν = 600and Gibbings (1959) proposed U1dT ν = 826 It should be noted that the criterion ofGibbings (1959) is based on a review of many data sets included those of Tani amp Sato(1956) and Fage amp Preston (1941) Gibbings (1959) expresses the Tani amp Sato (1956)and Fage amp Preston (1941) criteria as Reynolds numbers based on the freestream velocitywhich gives values of U1dT ν = 600 and 840 respectively The criterion given aboverepresent minimum values of the tripping device Reynolds number required to correctlytrip the boundary layer and agree with the results of Erm amp Joubert (1991)

An analysis of the literature for tests done on bodies of revolution indicated that thereis no consistent approach for selecting the size and type of device to use on such bodiesAppendix A gives details of devices used by different investigators for bodies of revolutiontogether with other experimental information Based on the freestream velocity and tripheight the Reynolds numbers of the trip devices given in Appendix A range from 200 to40 times 103 For the present investigation the approach used to establish the effects thatdifferent devices had on tripping laminar boundary layers was similar to that used byErm amp Joubert (1991) for a smooth flat plate in a zero pressure gradient Using theirtechnique it is possible to establish the size and type of tripping device to be used for agiven velocity to obtain correctly stimulated turbulent boundary layers

2 Preston-Tube Method of Measuring

Skin-Friction Coefficients

Skin-friction coefficients in a turbulent boundary layer flowing over a smooth surface canbe measured in a number of different ways (Fernholz et al 1996) including using Prestontubes (Preston 1954) from velocity profiles and using devices mounted flush with thesurface of a model Of the alternative approaches the Preston-tube method is convenientand is widely used The method makes use of a simple Pitot tube placed on the surfaceof a body and when used this way it is termed a Preston tube The method depends onan underlining assumption that in the region adjacent to the surface the flow is primarilydetermined by the surface shear stress and the properties of the fluid and is independentof factors such as pressure gradient and surface curvature The assumption implies thatthe velocity profile in a turbulent boundary layer adjacent to the surface is given by

U

Uτ= f

(Uτy

ν

)(1)

4 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

where U is the local stream-wise velocity Uτ is the friction velocity f is a universalfunction y is the wall normal coordinate and ν is the kinematic viscosity Equation (1) isoften referred to as the ldquolaw of the wallrdquo (Coles 1956)

A Pitot tube placed on the wall will measure a pressure relative to the wall staticpressure of ∆p = ρU22 at an effective coordinate y = c0d where d is the outer diameterof the Pitot tube and c0 is an unknown constant Substituting the values U =

radic(2∆pρ)

and y = cod into (1) yields a relationship between the wall shear stress fluid propertiesPreston-tube pressure difference and the tube diameter which is given by

2∆p

ρUτ2 =

[f

(Uτ c0d

ν

)]2 (2)

Alternatively for the purpose of measuring skin friction (2) can be expressed more con-veniently in the form

τ0d2

4ρν2= F

(∆pd2

4ρν2

)(3)

where c0 has been absorbed into the function F The function F represents the ldquocalibra-tionrdquo function for a Preston tube and several experimentally derived forms exist in theliterature (see Preston 1954 Patel 1965 Zagarola et al 2001) Generally the calibrationis determined by placing the Preston tube in a pipe flow where the wall shear stress (orfriction factor) can be determined accurately by measuring the pressure gradient in thepipe

For the data presented in this report the calibration of Patel (1965) was used todetermine the wall shear stress The calibration curve of Patel (1965) is given as follows

xlowast =ylowast + 2 log10(195ylowast + 410) for 55 ltUτd

2νlt 800 (4)

ylowast =08287 minus 01381xlowast + 01437xlowast2 minus 0006xlowast3 for 56 ltUτd

2νlt 55 and (5)

ylowast =1

2xlowast + 0037 for

Uτd

2νlt 56 (6)

where

xlowast = log10

(∆pd2

4ρν2

)and ylowast = log10

(τ0d

2

4ρν2

)

The local skin friction coefficient Cf is then found using

Cf =τ0

12ρU

21

(7)

where U1 is the streamwise velocity at the edge of the boundary layer

The calibration given by (4)-(6) is valid only for a hydrodynamically smooth surfaceA surface is considered hydrodynamically smooth provided that the height of surfaceroughness elements remain less than 5νUτ (Jimenez 2004) The minimum value of 5νUτthat was measured was approximately 4microm and the measured surface finish was found tobe an order of magnitude less than this value (Section 32) Hence the requirement of ahydrodynamically smooth surface is satisfied for this experiment

UNCLASSIFIED 5

DSTOndashTRndash2898 UNCLASSIFIED

The fundamental requirement for using a Preston tube is that the boundary layer isin a turbulent state and that the dimension of the Preston tube is such that it remainswithin the region where (1) is valid (ie from (4) Uτdν lt 1600) The diameter of thePreston tube for all experiments was d = 06 mm and this ensured that Uτdν remainedless than 1600 well within the range of the calibration (4)

It is known that for sufficiently strong pressure gradients the form of (1) changes (seeNickels 2004) Patel (1965) quantifies the effect of pressure gradients using the non-dimensional pressure gradient parameter1

p+x =ν

ρU3τ

dp

dx (8)

The error associated with using a Preston tube in pressure gradients is quantified by Patel(1965) and is given by the following inequalities

1 Adverse pressure gradient

Max Error 3 0 lt p+x lt 001 andUτd

νle 200 (9a)

Max Error 6 0 lt p+x lt 0015 andUτd

νle 250 (9b)

2 Favourable pressure gradient

Max Error 3 minus0005 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10a)

Max Error 6 minus0007 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10b)

The pressure gradient data are presented in Section 44 and were found to fall within thelimits of (9a) and (10a) indicating that the skin-friction coefficients are valid to withinplusmn3 This accuracy is similar to the alternative direct skin-friction measuring techniqueswhich typically achieve an accuracy of plusmn4 (Fernholz et al 1996)

The effect of model spanwise curvature on (4)-(6) is not quantified A reasonableassumption is that since the boundary layer thickness is much less than the model diameterthe effect of spanwise model curvature can be neglected

The Preston-tube method as outlined above requires that the boundary layer is in aturbulent state For this reason the method cannot be used to infer the skin friction atlocations were the boundary layer is in a laminar state However the ∆p values read by thePreston tube can be used to determine where laminar-to-turbulent transition occurs Theregion of transition is associated with a discontinuity in ∆p when plotted as a functionof streamwise coordinate x as shown by Erm amp Joubert (1991)

1for clarity we have adopted the notation for the pressure gradient parameter used by Nickels (2004)Patel (1965) uses the symbol ∆

6 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 4 LSWT Layout see Erm (2003)

3 Test Program

In this preliminary investigation four different tripping devices were used to investigatethe effect of the device on the skin-friction profile of a generic sub-scale submarine modelTests were conducted both with and without the tripping devices at a range of nominalfree-stream velocities Uinfin ranging from Uinfin = 40 to 70 ms to assess their effectivenessin tripping the boundary layer

31 Test Facility

The Low-Speed Wind Tunnel at DSTO is a closed circuit continuous flow tunnel with acontraction ratio of 41 The test section has an irregular octagonal shape with a heightof 213 m a width of 274 m and a length of 6553 m with a longitudinal turbulenceintensity of approximately 04 in the region where the models are tested (see Erm2003) An outline of the plan of the wind tunnel is shown in Figure 4 Free-streamvelocities were measured using static pressure rings at the upstream and downstreamends of the contraction A Pitot-static probe mounted on the side wall near the front ofthe working section was used to provide an independent measurement of the free-streamvelocity

32 Test Model

The sub-scale submarine model utilised in these tests is referred to as the Joubert modelsince the geometry is based on the work of Joubert (2004) and Joubert (2006) as well asLoid amp Bystrom (1983) The model was designed for the purpose of experimental and

UNCLASSIFIED 7

DSTOndashTRndash2898 UNCLASSIFIED

1

2 345

6 7 8 91011

12 13 141516

17 181920

212223

24 252627

28 29 303132

33 34

35

Top view

Side view

Figure 5 Schematic of scale model showing static-pressure port locations green and redmarkers represent the starboard and port static-pressure ports respectively

numerical studies and has no full-scale equivalent While the full model includes a casingcentre fin and control surfaces all tests reported here were conducted on the axisymmetricbody shape only

The model was machined from aluminum and consists of an ellipsoidal nose a cylin-drical centre-body and a streamlined tail section At the design stage an N6 surface finishwas specified for the model which corresponds to a roughness of 08microm in waviness Af-ter manufacture the surface finish was checked using a Surface Roughness Indicator andthe finish was found to be better than the design specification The model was anodisedwhich increased the thickness of the natural oxide layer by about 10microm

The model is 1350 mm long with a maximum diameter of 185 mm and slendernessratio of 73 where the slenderness ratio is defined as hull length divided by maximumhull diameter The model contains 21 longitudinal static-pressure ports on the centre-lineof the upper surface and 14 lateral static-pressure ports offset to the port and starboardsides of the upper surface centre-line Figure 5 shows the stream-wise location of thestatic-pressure ports

The model was supported by a single pylon as shown in Figure 6 All tests were carriedout at zero angle of yaw and zero angle of pitch The origin of the body coordinate systemis located at the nose of the submarine model The x-axis corresponds to the axis ofsymmetry of the model

8 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 6 Submarine model mounted in LSWT showing pylon support and pitch controlarm

UNCLASSIFIED 9

DSTOndashTRndash2898 UNCLASSIFIED

Table 1 Details of tripping devices where the Reynolds number is based on the height ofthe device The minimum Reynolds number and maximum Reynolds number correspondto nominal freestream velocities of Uinfin = 40 ms and Uinfin = 70 ms respectively where his the height of the grit and w is the width of the grit

Device Dimensions (mm) RedT (min) RedT (max)

Wire 1 dT = 01 281 496Wire 2 dT = 02 577 1015Wire 3 dT = 05 1443 256680 Grit h = 021 w = 3 605 1073

33 Tripping Devices

In this work four tripping devices were tested and consisted of circular wires with diame-ters dT = 01 02 and 05 mm as well as a distributed silicon carbide grit of size 80 havinga width of 3 mm The circular wires were bent to conform to the local diameter of thesubmarine and then attached with ldquosuper-gluerdquo such that there was no gap between thewire and the model surface Figure 7 The silicon carbide grit is prepared by distributinga layer of grit on double-sided sticky tape the tape is then adhered to the submarineFigure 8 The tripping devices were attached to the submarine model circumferentiallylocated at a streamwise coordinate of x = 675 mm measured from the nose of the sub-marine which corresponds to 5 of the total model length The dimensions of the tripdevices along with the Reynolds number range of the trip devices are summarised inTable 1 Note that the Reynolds number of the trip device is defined as RedT = U1dT νwhere for the case of the 80 grit dT is replaced by the grit height h

34 Pressure Scanners

Pressure Systems Incorporated (PSI) brand pressure scanners were used to measure allstatic and total pressures The pressure scanners are differential pressure measurementunits consisting of an array of silicon piezoresistive pressure sensors one for each pressureport The outputs of the sensors are electronically multiplexed through a single on-boardinstrumentation amplifier using binary addressing The scanners include a two-positioncalibration manifold actuated by momentary pulses of control pressures In the calibrateposition all sensors are connected to a common calibration pressure port A series ofaccurately-measured pressures is applied through this port to characterize the sensorsProper and periodic on-line calibration maintains static errors within plusmn003 or betterof the full-scale pressure range

The pressure scanners are controlled and sampled using a PSI 8400 electronic measure-ment system It is a modular parallel processing system for high-speed pressure scanningat up to 20000 measurements per second and allows the use of digitally temperaturecompensated pressure scanners

Two differential pressure scanners were used in the experiments All pressures aremeasured relative to the free-stream static pressure pinfin as measured by the referencefree-stream Pitot-static probe Each pressure scanner contained 32 ports The full-scale

10 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 7 Location of trip wire

Figure 8 Photo showing the 3 mm wide band of 80 grit transition strip

UNCLASSIFIED 11

DSTOndashTRndash2898 UNCLASSIFIED

pressure range of the scanners is 249 kPa (ldquo10 inches-of-water scannerrdquo) and 689 kPa(ldquo1 psi scannerrdquo) The 689 kPa scanner was used to read the static pressure at the longi-tudinal ports as well as the output from the Preston tube and the Pitot-static probe

For the purpose of cross-checking and for redundancy the Preston tube was connectedto two independent ports of the 689 kPa scanner and the two readings averaged For thisscanner pressures could be read to an accuracy of 6890 times 00003 Pa ie about 2 Pa Theminimum ∆p measured by the Preston tube was 145 Pa which gives a pressure scannerresolution of 14 However this minimum ∆p was recorded for a location where thePreston tube was in a laminar boundary layer and such data is only useful in a qualitativesense (see Section 2) For locations were the boundary layer is turbulent the minimum ∆pwas 340 Pa which gives a pressure scanner resolution of 06 The 249 kPa scanner wasused mainly to acquire the static pressures at the lateral ports

35 Data Acquisition Software

A software package called ImPressOne was used which communicates with the PSI 8400and displays and acquires the pressure data for the model under test For the staticpressure measurements 100 readings were acquired at each pressure port at a samplingrate of 20 Hz For the Preston-tube measurements the sample rate was increased and100 samples were acquired at each pressure port at a sampling rate of 50 Hz for eachfree-stream velocity

36 Experimental Procedure

The hull was tested with each of the selected tripping devices listed in Table 1 as wellas without a tripping device resulting in five different test configurations For each testconfiguration the static pressures were initially acquired for that particular configurationfollowed by the Preston-tube measurements

A Preston tube having a diameter of 06 mm was attached to the surface of the modelusing both plasticine and tape to ensure that the tube was positioned as flat as possibleon the surface of the model as shown in Figure 9 Preston-tube measurement were takenon the upper surface of the submarine model along a line directly above the centre-lineof the model For the dT = 02 and 05 mm wires and the grit case measurements weretaken from x = 73 mm to x = 1065 mm for a total of 18 stations For the dT = 01 mmwire measurements were limited to 3 stations between x = 305 mm and x = 442 mmThe stream-wise coordinates for the Preston tube measurements are given in the Table 2Data were acquired for a range of free-stream velocities from 40 to 70 ms in incrementsof 5 ms

For each nominal velocity the corresponding model Reynolds number was calcu-lated assuming standard temperature and atmospheric pressure conditions 20C and101 325 Pa respectively For each given test the temperature and static pressure of theair within the test section were logged and the air density and viscosity were calculatedTo account for daily variations in temperature and atmospheric pressure the freestream

12 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Flow direction

Figure 9 Preston tube located on the centre-line of the upper-surface of submarine

velocity was adjusted to ensure that the model Reynolds number remained constant foreach given nominal velocity condition as shown in Table 3

Table 2 Skin-friction measurement stations Where applicable the corresponding staticport number is given For the dT = 01 mm wire measurements were only taken at stations3050 3600 as well as an additional station at x = 4425 mm

xmm 731 787 843 900 1125 1350 1575 1800 2150Static port - - - 6 - 7 - 8 -

xmm 2500 3050 3600 5250 7000 8700 9500 10100 10650Static port 9 - 12 13 14 17 18 21 24

Table 3 Reynolds numbers (based on submarine length 135 m) corresponding to thenominal free-stream velocities

Nominal Uinfin 40 45 50 55 60 65 70 msRe 358 403 448 493 537 582 627 times106

37 Data Reduction

The static pressure readings from the pressure ports were converted to pressure coefficientsusing the relationship

Cp =ps minus pinfinpt minus pinfin

(11)

where pinfin is the reference free-stream static pressure pt is the reference free-stream totalpressure and ps is the static pressure on the surface of the submarine model

As explained in Section 34 all Preston tube pressures are measured relative to the free-stream static pressure In order to apply the Preston tube calibration (4)-(6) the loggedPreston-tube pressure differences (ie pp minus pinfin) must first be converted to a ∆p = pp minus ps

UNCLASSIFIED 13

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 4: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

THIS PAGE IS INTENTIONALLY BLANK

iv UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Authors

Malcolm JonesAerospace Division

Malcolm Jones obtained a Bachelor of Engineering (Mechani-cal) degree in 1994 and a PhD in 1998 both from The Uni-versity of Melbourne His PhD involved an experimental andtheoretical study of a turbulent boundary layer developing in anaccelerated flow He joined the Defence Science and TechnologyOrganisation in 2007 where he is currently employed as a Re-search Scientist in Aerospace Division While at DSTO he hasbeen involved in aerodynamic testing of aircraft models such asthe F-35 and AP-3C in the Low Speed Wind Tunnel aeroacous-tic measurements and analysis of cavity flows and aerodynamicand structural measurements of flapping wings Prior to joiningDSTO he was employed as Research Fellow and then lecturerin the Department of Mechanical Engineering at The Univer-sity of Melbourne (1999-2003) From 2004-2007 he worked atthe School of Mathematical Sciences Queensland University ofTechnology During his academic appointments he gave lec-ture courses in fluid mechanics heat transfer manufacturingand mathematics and undertook research in turbulent bound-ary layer flows and biological fluid mechanics

UNCLASSIFIED v

DSTOndashTRndash2898 UNCLASSIFIED

Lincoln ErmAerospace Division

Lincoln Erm obtained a Bachelor of Engineering (Mechanical)degree in 1967 and a Master of Engineering Science degree in1969 both from the University of Melbourne His Masterrsquos de-gree was concerned with the yielding of aluminium alloy whensubjected to both tensile and torsional loading He joined theAeronautical Research Laboratories (now called the DefenceScience and Technology Organisation) in 1970 and has workedon a wide range of research projects including the prediction ofthe performance of gas-turbine engines under conditions of pul-sating flow parametric studies of ramrocket performance flowinstability in aircraft intakes and problems associated with thelanding of a helicopter on the flight deck of a ship Concurrentlywith some of the above work he studied at the University ofMelbourne and in 1988 obtained his Doctor of Philosophy de-gree for work on low-Reynolds-number turbulent boundary lay-ers Since this time he has undertaken research investigationsin the low-speed wind tunnel and the water tunnel Recentwork has been concerned with extending the testing capabili-ties of the water tunnel including developing a two-componentstrain-gauge-balance load-measurement system for the tunneland developing a dynamic-testing capability for the tunnel en-abling aerodynamic derivatives to be measured on models

Aliya ValiyffAerospace Division

Aliya Valiyff graduated from the University of Adelaide in 2009with a Bachelor of Aerospace Engineering and Bachelor of Sci-ence (Applied Mathematics and Physics) with 1st class honoursShe commenced work with DSTO in 2010 and during her timeshe has mainly worked within the Unmanned Aerial System -Corporate Enabling Research Programme (CERP) undertak-ing research on flapping wing and the flight and the UnderseaWarfare- CERP

vi UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Simon HenbestAerospace Division

Simon Henbest obtained a Bachelor of Engineering (Mechan-ical) degree with honours in 1977 and a PhD in 1983 bothfrom The University of Melbourne His PhD titled rdquoThe Struc-ture of Turbulent Pipe Flowrdquo provide experimental support toTownsendrsquos attached eddy hypothesis for wall bounded flowsIn 1984 he was awarded an Australian National Research Fel-lowship and continued wall turbulence research at the Univer-sity of Melbourne In 1987 he commenced employment at theAeronautical Research Laboratories (now called the DefenceScience and Technology Organisation) and obtained merit pro-motions to both Senior Research Scientist and Principal Re-search Scientist While at DSTO he has been involved in re-search into high speed jet and aeroacoustic cavity flows the IRsignature prediction of aircraft numerous aerodynamic testingprogrammes He has acted as a Research Leader for extendedperiods in AVD AOD and HPPD He is currently Head of FluidMechanics in Aerospace Division

UNCLASSIFIED vii

DSTOndashTRndash2898 UNCLASSIFIED

THIS PAGE IS INTENTIONALLY BLANK

viii UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Contents

Glossary xi

Notation xi

1 Introduction 1

11 Boundary-Layer Transition 1

12 Approach of Erm amp Joubert (1991) 2

13 Empirical Expressions to Determine Sizes of Tripping Devices 4

2 Preston-Tube Method of Measuring Skin-Friction Coefficients 4

3 Test Program 7

31 Test Facility 7

32 Test Model 7

33 Tripping Devices 10

34 Pressure Scanners 10

35 Data Acquisition Software 12

36 Experimental Procedure 12

37 Data Reduction 13

4 Results 14

41 Skin Friction Without a Tripping Device 14

42 Skin Friction With Tripping Devices 16

421 Comparison of the Different Trip Devices 21

422 Scaling of Skin Friction with Reynolds Number 22

423 Over-stimulation and the Maximum Trip Reynolds Number 23

43 Pressure Coefficients 24

44 Pressure Gradients 26

5 Comparison with CFD Predictions 29

6 Conclusions 30

7 Acknowledgements 32

Appendices

UNCLASSIFIED ix

DSTOndashTRndash2898 UNCLASSIFIED

A Summary of Tripping Devices Used in Previous Experiments 35

B Preston Tube Data Processing 36

C Skin Friction Coefficients 37

D Pressure Coefficients 45

x UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Glossary

DARPA Defense Advanced Research Projects AgencyCERP Corporate Enabling Research ProgramCFD Computational Fluid DynamicsLSWT Low-Speed Wind TunnelDSTO Defence Science and Technology Organisation

Notation

Cf Local skin-friction coefficientCp Pressure coefficientd Outer diameter of Preston tubedT Diameter of trip wireh Height of grit transition strippinfin Free-stream static pressurepp Total pressure of Preston tubeps Model surface static pressurept Free-stream total pressurep+x Non-dimensional pressure gradient parameterRe Reynolds numberRedT Reynolds number based on diameter of wireRex Reynolds number based on the stream-wise coordinateRext Streamwise Reynolds number of transition pointU Streamwise velocity in boundary layerU1 Streamwise velocity at edge of boundary layerUinfin Nominal streamwise velocity in tunnel working-sectionUτ Friction velocityw Width of grit transition stripx Streamwise coordinatext Streamwise coordinate of transition pointy Wall normal coordinate∆p ∆p = pp minus psν Kinematic viscosityρ Fluid densityτ0 Wall shear stress

UNCLASSIFIED xi

DSTOndashTRndash2898 UNCLASSIFIED

THIS PAGE IS INTENTIONALLY BLANK

xii UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

1 Introduction

This work aims to understand flow fields about a submarine As part of this programa series of experiments have been conducted in the Low-Speed Wind Tunnel (LSWT) atthe Defence Science and Technology Organisation (DSTO) to quantify the skin-frictiondistributions on a generic submarine model and in the process investigate the effectivenessof a limited range of tripping devices The results also provide a reference data set forcomputational fluid dynamics (CFD) validation of a submarine model

When conducting tests in wind tunnels on a sub-scale model for results of the exper-iment to be transferable to the full-scale vehicle the flow patterns and load coefficientson the model and the full-size vehicle need to be made similar Ideally this is achievedthrough matching the Reynolds number of the flow over the model to that of the full-scalevehicle However in practice this is difficult to achieve and is not always possible To en-sure that the flow features on the model are representative of those for the full-size vehiclea tripping device can be used such that the boundary layers (ie regions of laminar flowlaminar-to-turbulent transition and turbulent flow) are made similar However differenttripping devices can impart different disturbances into the flow In order to correctly stim-ulate the boundary layer on the submarine model and avoid over- or under-stimulationthe type and size of tripping devices need to be selected for a given Reynolds numberor Reynolds number range and also for a specific trip location Additionally the chosentripping device will be specific to a given tunnel and would be dependent on factors suchas the level of free-stream turbulence in the tunnel

dT

Ud

Trip wire

xd

Laminar Transition Turbulent

Boundary-layeredge

U1

Figure 1 Diagrammatic representation of a boundary layer being tripped based on adiagram given by White (1974)

11 Boundary-Layer Transition

Boundary-layer transition is a complicated physical process dependent on instability mech-anisms including Tollmien-Schlichting waves crossflow and Gortler instabilities (see Reedamp Saric 2008) Over the years there have been numerous articles published on transi-tion both from experimental investigations and CFD analyses in low-speed transonic

UNCLASSIFIED 1

DSTOndashTRndash2898 UNCLASSIFIED

and hypersonic flow regimes (for example Schlatter amp Henningson 2009) Details of thetransition process are still not fully understood In the present report transition physicalprocesses are not considered instead attention is focused on how to stabilise the posi-tion of the transition using a tripping device and to ensure that the turbulent boundarylayer is neither under- or over-stimulated irrespective of the flow physics associated withtransition

12 Approach of Erm amp Joubert (1991)

A diagrammatic representation of a boundary layer being tripped is shown in Figure 1where dT is the height of the tripping device U1 is the streamwise velocity at the edge ofthe boundary layer xd is the location of the tripping device measured from the nose ofthe model and Ud is the velocity in the boundary layer at the top of the device

A question that had to be addressed was what is the best size and type of trippingdevice to use in the current experiments in the LSWT to trip the boundary layer on thesubmarine model Erm amp Joubert (1991) faced a similar question in their studies on low-Reynolds-number flows over a smooth flat surface in a zero pressure gradient For differenttypes of tripping devices they measured longitudinal skin-friction coefficients for a rangeof free-stream velocities Their data for a 12 mm wire tripping device are reproduced inFigure 2 From this figure it can be seen that as the velocity is increased from 8 ms thedevice imparts an increased amount of turbulent energy into the flow so that the laminar-to-turbulent transition region moves upstream They conjectured that correct stimulationis associated with a particular curve when the peaks of successive curves correspondingto higher velocities do not advance significantly upstream Velocities lower than thatcorresponding to the particular curve were obviously associated with under-stimulatedflows since the peaks of the curves were well downstream of the device and thus thedevice was therefore not completely effective in tripping the flow Since the velocitycorresponding to the particular curve establishes a turbulent boundary layer almost to thepossible upstream limit of turbulent flow it seemed reasonable to assume that the maineffect of higher velocities was to overstimulate the flow

The x-coordinate corresponding to the peaks of Figure 2 are plotted in Figure 3 as afunction of streamwise velocity and it is apparent that the above condition for correct stim-ulation was satisfied when the velocity was between 10 and 12 ms This corresponds to aminimum Reynolds number of the tripping device in the range of RedT = U1dT ν = 800to 960 where ν is the kinematic viscosity For the case where a trip device has aReynolds number greater than the minimum required the tripping device may overstim-ulate the flow Note over-stimulation does not necessarily result in higher skin-frictionwhen compared to a correctly stimulated layer Rather it means that the disturbanceintroduced by the tripping device is felt downstream of the transition region and leadsto a ldquonon-standardrdquo turbulent boundary initially developing Ideally to assess whetherover-stimulation has occurred complete velocity profiles in the turbulent region need tobe measured and compared against reference data sets such as those collated by Coles(1962)

It should be noted that in the current work the boundary layer develops in a pressuregradient with wall curvature in both the streamwise and spanwise directions Whereas

2 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

the work of Erm amp Joubert (1991) was undertaken on a flat plate zero pressure gradientthis means the RedT values given above cannot be applied directly to predict the trip sizerequired However the approach taken here broadly follows that of Erm amp Joubert (1991)in that a range of trip Reynolds numbers were tested (by varying both freestream velocityand trip size) and the skin-friction downstream of the trip measured

0 01 02x (m)

03 04 05

Figure 2 Cf vs x measurements for a 12 mm diameter trip wire for different free-streamvelocities as obtained by Erm amp Joubert (1991)

8 9 10 11 12 13 14

xlocation

(m)of

peakCf

Location of peak Cf

Location of trip device

01

02

0

Uinfin (ms)

Figure 3 Location of the peak Cf values shown in Figure 2

UNCLASSIFIED 3

DSTOndashTRndash2898 UNCLASSIFIED

13 Empirical Expressions to Determine Sizes of TrippingDevices

Researchers have proposed different empirical expressions for determining the size of deviceto use to trip the flow The relationships incorporate parameters including the height ofthe tripping device dT the velocity at the edge of the boundary layer U1 the velocity inthe undisturbed boundary layer at the top of the device Ud and the wall friction velocityevaluated at the device Uτ The friction velocity is defined by τ0 = ρU2

τ where τ0 is thesurface shear stress and ρ is the fluid density Recommendations for fully-effective trippingcover quite a wide range Tani et al (1940) proposed the criterion UτdT ν = 13 Fage ampPreston (1941) proposed UτdT ν = 20 Braslow amp Knox (1958) proposed UddT ν = 600and Gibbings (1959) proposed U1dT ν = 826 It should be noted that the criterion ofGibbings (1959) is based on a review of many data sets included those of Tani amp Sato(1956) and Fage amp Preston (1941) Gibbings (1959) expresses the Tani amp Sato (1956)and Fage amp Preston (1941) criteria as Reynolds numbers based on the freestream velocitywhich gives values of U1dT ν = 600 and 840 respectively The criterion given aboverepresent minimum values of the tripping device Reynolds number required to correctlytrip the boundary layer and agree with the results of Erm amp Joubert (1991)

An analysis of the literature for tests done on bodies of revolution indicated that thereis no consistent approach for selecting the size and type of device to use on such bodiesAppendix A gives details of devices used by different investigators for bodies of revolutiontogether with other experimental information Based on the freestream velocity and tripheight the Reynolds numbers of the trip devices given in Appendix A range from 200 to40 times 103 For the present investigation the approach used to establish the effects thatdifferent devices had on tripping laminar boundary layers was similar to that used byErm amp Joubert (1991) for a smooth flat plate in a zero pressure gradient Using theirtechnique it is possible to establish the size and type of tripping device to be used for agiven velocity to obtain correctly stimulated turbulent boundary layers

2 Preston-Tube Method of Measuring

Skin-Friction Coefficients

Skin-friction coefficients in a turbulent boundary layer flowing over a smooth surface canbe measured in a number of different ways (Fernholz et al 1996) including using Prestontubes (Preston 1954) from velocity profiles and using devices mounted flush with thesurface of a model Of the alternative approaches the Preston-tube method is convenientand is widely used The method makes use of a simple Pitot tube placed on the surfaceof a body and when used this way it is termed a Preston tube The method depends onan underlining assumption that in the region adjacent to the surface the flow is primarilydetermined by the surface shear stress and the properties of the fluid and is independentof factors such as pressure gradient and surface curvature The assumption implies thatthe velocity profile in a turbulent boundary layer adjacent to the surface is given by

U

Uτ= f

(Uτy

ν

)(1)

4 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

where U is the local stream-wise velocity Uτ is the friction velocity f is a universalfunction y is the wall normal coordinate and ν is the kinematic viscosity Equation (1) isoften referred to as the ldquolaw of the wallrdquo (Coles 1956)

A Pitot tube placed on the wall will measure a pressure relative to the wall staticpressure of ∆p = ρU22 at an effective coordinate y = c0d where d is the outer diameterof the Pitot tube and c0 is an unknown constant Substituting the values U =

radic(2∆pρ)

and y = cod into (1) yields a relationship between the wall shear stress fluid propertiesPreston-tube pressure difference and the tube diameter which is given by

2∆p

ρUτ2 =

[f

(Uτ c0d

ν

)]2 (2)

Alternatively for the purpose of measuring skin friction (2) can be expressed more con-veniently in the form

τ0d2

4ρν2= F

(∆pd2

4ρν2

)(3)

where c0 has been absorbed into the function F The function F represents the ldquocalibra-tionrdquo function for a Preston tube and several experimentally derived forms exist in theliterature (see Preston 1954 Patel 1965 Zagarola et al 2001) Generally the calibrationis determined by placing the Preston tube in a pipe flow where the wall shear stress (orfriction factor) can be determined accurately by measuring the pressure gradient in thepipe

For the data presented in this report the calibration of Patel (1965) was used todetermine the wall shear stress The calibration curve of Patel (1965) is given as follows

xlowast =ylowast + 2 log10(195ylowast + 410) for 55 ltUτd

2νlt 800 (4)

ylowast =08287 minus 01381xlowast + 01437xlowast2 minus 0006xlowast3 for 56 ltUτd

2νlt 55 and (5)

ylowast =1

2xlowast + 0037 for

Uτd

2νlt 56 (6)

where

xlowast = log10

(∆pd2

4ρν2

)and ylowast = log10

(τ0d

2

4ρν2

)

The local skin friction coefficient Cf is then found using

Cf =τ0

12ρU

21

(7)

where U1 is the streamwise velocity at the edge of the boundary layer

The calibration given by (4)-(6) is valid only for a hydrodynamically smooth surfaceA surface is considered hydrodynamically smooth provided that the height of surfaceroughness elements remain less than 5νUτ (Jimenez 2004) The minimum value of 5νUτthat was measured was approximately 4microm and the measured surface finish was found tobe an order of magnitude less than this value (Section 32) Hence the requirement of ahydrodynamically smooth surface is satisfied for this experiment

UNCLASSIFIED 5

DSTOndashTRndash2898 UNCLASSIFIED

The fundamental requirement for using a Preston tube is that the boundary layer isin a turbulent state and that the dimension of the Preston tube is such that it remainswithin the region where (1) is valid (ie from (4) Uτdν lt 1600) The diameter of thePreston tube for all experiments was d = 06 mm and this ensured that Uτdν remainedless than 1600 well within the range of the calibration (4)

It is known that for sufficiently strong pressure gradients the form of (1) changes (seeNickels 2004) Patel (1965) quantifies the effect of pressure gradients using the non-dimensional pressure gradient parameter1

p+x =ν

ρU3τ

dp

dx (8)

The error associated with using a Preston tube in pressure gradients is quantified by Patel(1965) and is given by the following inequalities

1 Adverse pressure gradient

Max Error 3 0 lt p+x lt 001 andUτd

νle 200 (9a)

Max Error 6 0 lt p+x lt 0015 andUτd

νle 250 (9b)

2 Favourable pressure gradient

Max Error 3 minus0005 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10a)

Max Error 6 minus0007 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10b)

The pressure gradient data are presented in Section 44 and were found to fall within thelimits of (9a) and (10a) indicating that the skin-friction coefficients are valid to withinplusmn3 This accuracy is similar to the alternative direct skin-friction measuring techniqueswhich typically achieve an accuracy of plusmn4 (Fernholz et al 1996)

The effect of model spanwise curvature on (4)-(6) is not quantified A reasonableassumption is that since the boundary layer thickness is much less than the model diameterthe effect of spanwise model curvature can be neglected

The Preston-tube method as outlined above requires that the boundary layer is in aturbulent state For this reason the method cannot be used to infer the skin friction atlocations were the boundary layer is in a laminar state However the ∆p values read by thePreston tube can be used to determine where laminar-to-turbulent transition occurs Theregion of transition is associated with a discontinuity in ∆p when plotted as a functionof streamwise coordinate x as shown by Erm amp Joubert (1991)

1for clarity we have adopted the notation for the pressure gradient parameter used by Nickels (2004)Patel (1965) uses the symbol ∆

6 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 4 LSWT Layout see Erm (2003)

3 Test Program

In this preliminary investigation four different tripping devices were used to investigatethe effect of the device on the skin-friction profile of a generic sub-scale submarine modelTests were conducted both with and without the tripping devices at a range of nominalfree-stream velocities Uinfin ranging from Uinfin = 40 to 70 ms to assess their effectivenessin tripping the boundary layer

31 Test Facility

The Low-Speed Wind Tunnel at DSTO is a closed circuit continuous flow tunnel with acontraction ratio of 41 The test section has an irregular octagonal shape with a heightof 213 m a width of 274 m and a length of 6553 m with a longitudinal turbulenceintensity of approximately 04 in the region where the models are tested (see Erm2003) An outline of the plan of the wind tunnel is shown in Figure 4 Free-streamvelocities were measured using static pressure rings at the upstream and downstreamends of the contraction A Pitot-static probe mounted on the side wall near the front ofthe working section was used to provide an independent measurement of the free-streamvelocity

32 Test Model

The sub-scale submarine model utilised in these tests is referred to as the Joubert modelsince the geometry is based on the work of Joubert (2004) and Joubert (2006) as well asLoid amp Bystrom (1983) The model was designed for the purpose of experimental and

UNCLASSIFIED 7

DSTOndashTRndash2898 UNCLASSIFIED

1

2 345

6 7 8 91011

12 13 141516

17 181920

212223

24 252627

28 29 303132

33 34

35

Top view

Side view

Figure 5 Schematic of scale model showing static-pressure port locations green and redmarkers represent the starboard and port static-pressure ports respectively

numerical studies and has no full-scale equivalent While the full model includes a casingcentre fin and control surfaces all tests reported here were conducted on the axisymmetricbody shape only

The model was machined from aluminum and consists of an ellipsoidal nose a cylin-drical centre-body and a streamlined tail section At the design stage an N6 surface finishwas specified for the model which corresponds to a roughness of 08microm in waviness Af-ter manufacture the surface finish was checked using a Surface Roughness Indicator andthe finish was found to be better than the design specification The model was anodisedwhich increased the thickness of the natural oxide layer by about 10microm

The model is 1350 mm long with a maximum diameter of 185 mm and slendernessratio of 73 where the slenderness ratio is defined as hull length divided by maximumhull diameter The model contains 21 longitudinal static-pressure ports on the centre-lineof the upper surface and 14 lateral static-pressure ports offset to the port and starboardsides of the upper surface centre-line Figure 5 shows the stream-wise location of thestatic-pressure ports

The model was supported by a single pylon as shown in Figure 6 All tests were carriedout at zero angle of yaw and zero angle of pitch The origin of the body coordinate systemis located at the nose of the submarine model The x-axis corresponds to the axis ofsymmetry of the model

8 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 6 Submarine model mounted in LSWT showing pylon support and pitch controlarm

UNCLASSIFIED 9

DSTOndashTRndash2898 UNCLASSIFIED

Table 1 Details of tripping devices where the Reynolds number is based on the height ofthe device The minimum Reynolds number and maximum Reynolds number correspondto nominal freestream velocities of Uinfin = 40 ms and Uinfin = 70 ms respectively where his the height of the grit and w is the width of the grit

Device Dimensions (mm) RedT (min) RedT (max)

Wire 1 dT = 01 281 496Wire 2 dT = 02 577 1015Wire 3 dT = 05 1443 256680 Grit h = 021 w = 3 605 1073

33 Tripping Devices

In this work four tripping devices were tested and consisted of circular wires with diame-ters dT = 01 02 and 05 mm as well as a distributed silicon carbide grit of size 80 havinga width of 3 mm The circular wires were bent to conform to the local diameter of thesubmarine and then attached with ldquosuper-gluerdquo such that there was no gap between thewire and the model surface Figure 7 The silicon carbide grit is prepared by distributinga layer of grit on double-sided sticky tape the tape is then adhered to the submarineFigure 8 The tripping devices were attached to the submarine model circumferentiallylocated at a streamwise coordinate of x = 675 mm measured from the nose of the sub-marine which corresponds to 5 of the total model length The dimensions of the tripdevices along with the Reynolds number range of the trip devices are summarised inTable 1 Note that the Reynolds number of the trip device is defined as RedT = U1dT νwhere for the case of the 80 grit dT is replaced by the grit height h

34 Pressure Scanners

Pressure Systems Incorporated (PSI) brand pressure scanners were used to measure allstatic and total pressures The pressure scanners are differential pressure measurementunits consisting of an array of silicon piezoresistive pressure sensors one for each pressureport The outputs of the sensors are electronically multiplexed through a single on-boardinstrumentation amplifier using binary addressing The scanners include a two-positioncalibration manifold actuated by momentary pulses of control pressures In the calibrateposition all sensors are connected to a common calibration pressure port A series ofaccurately-measured pressures is applied through this port to characterize the sensorsProper and periodic on-line calibration maintains static errors within plusmn003 or betterof the full-scale pressure range

The pressure scanners are controlled and sampled using a PSI 8400 electronic measure-ment system It is a modular parallel processing system for high-speed pressure scanningat up to 20000 measurements per second and allows the use of digitally temperaturecompensated pressure scanners

Two differential pressure scanners were used in the experiments All pressures aremeasured relative to the free-stream static pressure pinfin as measured by the referencefree-stream Pitot-static probe Each pressure scanner contained 32 ports The full-scale

10 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 7 Location of trip wire

Figure 8 Photo showing the 3 mm wide band of 80 grit transition strip

UNCLASSIFIED 11

DSTOndashTRndash2898 UNCLASSIFIED

pressure range of the scanners is 249 kPa (ldquo10 inches-of-water scannerrdquo) and 689 kPa(ldquo1 psi scannerrdquo) The 689 kPa scanner was used to read the static pressure at the longi-tudinal ports as well as the output from the Preston tube and the Pitot-static probe

For the purpose of cross-checking and for redundancy the Preston tube was connectedto two independent ports of the 689 kPa scanner and the two readings averaged For thisscanner pressures could be read to an accuracy of 6890 times 00003 Pa ie about 2 Pa Theminimum ∆p measured by the Preston tube was 145 Pa which gives a pressure scannerresolution of 14 However this minimum ∆p was recorded for a location where thePreston tube was in a laminar boundary layer and such data is only useful in a qualitativesense (see Section 2) For locations were the boundary layer is turbulent the minimum ∆pwas 340 Pa which gives a pressure scanner resolution of 06 The 249 kPa scanner wasused mainly to acquire the static pressures at the lateral ports

35 Data Acquisition Software

A software package called ImPressOne was used which communicates with the PSI 8400and displays and acquires the pressure data for the model under test For the staticpressure measurements 100 readings were acquired at each pressure port at a samplingrate of 20 Hz For the Preston-tube measurements the sample rate was increased and100 samples were acquired at each pressure port at a sampling rate of 50 Hz for eachfree-stream velocity

36 Experimental Procedure

The hull was tested with each of the selected tripping devices listed in Table 1 as wellas without a tripping device resulting in five different test configurations For each testconfiguration the static pressures were initially acquired for that particular configurationfollowed by the Preston-tube measurements

A Preston tube having a diameter of 06 mm was attached to the surface of the modelusing both plasticine and tape to ensure that the tube was positioned as flat as possibleon the surface of the model as shown in Figure 9 Preston-tube measurement were takenon the upper surface of the submarine model along a line directly above the centre-lineof the model For the dT = 02 and 05 mm wires and the grit case measurements weretaken from x = 73 mm to x = 1065 mm for a total of 18 stations For the dT = 01 mmwire measurements were limited to 3 stations between x = 305 mm and x = 442 mmThe stream-wise coordinates for the Preston tube measurements are given in the Table 2Data were acquired for a range of free-stream velocities from 40 to 70 ms in incrementsof 5 ms

For each nominal velocity the corresponding model Reynolds number was calcu-lated assuming standard temperature and atmospheric pressure conditions 20C and101 325 Pa respectively For each given test the temperature and static pressure of theair within the test section were logged and the air density and viscosity were calculatedTo account for daily variations in temperature and atmospheric pressure the freestream

12 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Flow direction

Figure 9 Preston tube located on the centre-line of the upper-surface of submarine

velocity was adjusted to ensure that the model Reynolds number remained constant foreach given nominal velocity condition as shown in Table 3

Table 2 Skin-friction measurement stations Where applicable the corresponding staticport number is given For the dT = 01 mm wire measurements were only taken at stations3050 3600 as well as an additional station at x = 4425 mm

xmm 731 787 843 900 1125 1350 1575 1800 2150Static port - - - 6 - 7 - 8 -

xmm 2500 3050 3600 5250 7000 8700 9500 10100 10650Static port 9 - 12 13 14 17 18 21 24

Table 3 Reynolds numbers (based on submarine length 135 m) corresponding to thenominal free-stream velocities

Nominal Uinfin 40 45 50 55 60 65 70 msRe 358 403 448 493 537 582 627 times106

37 Data Reduction

The static pressure readings from the pressure ports were converted to pressure coefficientsusing the relationship

Cp =ps minus pinfinpt minus pinfin

(11)

where pinfin is the reference free-stream static pressure pt is the reference free-stream totalpressure and ps is the static pressure on the surface of the submarine model

As explained in Section 34 all Preston tube pressures are measured relative to the free-stream static pressure In order to apply the Preston tube calibration (4)-(6) the loggedPreston-tube pressure differences (ie pp minus pinfin) must first be converted to a ∆p = pp minus ps

UNCLASSIFIED 13

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 5: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

Authors

Malcolm JonesAerospace Division

Malcolm Jones obtained a Bachelor of Engineering (Mechani-cal) degree in 1994 and a PhD in 1998 both from The Uni-versity of Melbourne His PhD involved an experimental andtheoretical study of a turbulent boundary layer developing in anaccelerated flow He joined the Defence Science and TechnologyOrganisation in 2007 where he is currently employed as a Re-search Scientist in Aerospace Division While at DSTO he hasbeen involved in aerodynamic testing of aircraft models such asthe F-35 and AP-3C in the Low Speed Wind Tunnel aeroacous-tic measurements and analysis of cavity flows and aerodynamicand structural measurements of flapping wings Prior to joiningDSTO he was employed as Research Fellow and then lecturerin the Department of Mechanical Engineering at The Univer-sity of Melbourne (1999-2003) From 2004-2007 he worked atthe School of Mathematical Sciences Queensland University ofTechnology During his academic appointments he gave lec-ture courses in fluid mechanics heat transfer manufacturingand mathematics and undertook research in turbulent bound-ary layer flows and biological fluid mechanics

UNCLASSIFIED v

DSTOndashTRndash2898 UNCLASSIFIED

Lincoln ErmAerospace Division

Lincoln Erm obtained a Bachelor of Engineering (Mechanical)degree in 1967 and a Master of Engineering Science degree in1969 both from the University of Melbourne His Masterrsquos de-gree was concerned with the yielding of aluminium alloy whensubjected to both tensile and torsional loading He joined theAeronautical Research Laboratories (now called the DefenceScience and Technology Organisation) in 1970 and has workedon a wide range of research projects including the prediction ofthe performance of gas-turbine engines under conditions of pul-sating flow parametric studies of ramrocket performance flowinstability in aircraft intakes and problems associated with thelanding of a helicopter on the flight deck of a ship Concurrentlywith some of the above work he studied at the University ofMelbourne and in 1988 obtained his Doctor of Philosophy de-gree for work on low-Reynolds-number turbulent boundary lay-ers Since this time he has undertaken research investigationsin the low-speed wind tunnel and the water tunnel Recentwork has been concerned with extending the testing capabili-ties of the water tunnel including developing a two-componentstrain-gauge-balance load-measurement system for the tunneland developing a dynamic-testing capability for the tunnel en-abling aerodynamic derivatives to be measured on models

Aliya ValiyffAerospace Division

Aliya Valiyff graduated from the University of Adelaide in 2009with a Bachelor of Aerospace Engineering and Bachelor of Sci-ence (Applied Mathematics and Physics) with 1st class honoursShe commenced work with DSTO in 2010 and during her timeshe has mainly worked within the Unmanned Aerial System -Corporate Enabling Research Programme (CERP) undertak-ing research on flapping wing and the flight and the UnderseaWarfare- CERP

vi UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Simon HenbestAerospace Division

Simon Henbest obtained a Bachelor of Engineering (Mechan-ical) degree with honours in 1977 and a PhD in 1983 bothfrom The University of Melbourne His PhD titled rdquoThe Struc-ture of Turbulent Pipe Flowrdquo provide experimental support toTownsendrsquos attached eddy hypothesis for wall bounded flowsIn 1984 he was awarded an Australian National Research Fel-lowship and continued wall turbulence research at the Univer-sity of Melbourne In 1987 he commenced employment at theAeronautical Research Laboratories (now called the DefenceScience and Technology Organisation) and obtained merit pro-motions to both Senior Research Scientist and Principal Re-search Scientist While at DSTO he has been involved in re-search into high speed jet and aeroacoustic cavity flows the IRsignature prediction of aircraft numerous aerodynamic testingprogrammes He has acted as a Research Leader for extendedperiods in AVD AOD and HPPD He is currently Head of FluidMechanics in Aerospace Division

UNCLASSIFIED vii

DSTOndashTRndash2898 UNCLASSIFIED

THIS PAGE IS INTENTIONALLY BLANK

viii UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Contents

Glossary xi

Notation xi

1 Introduction 1

11 Boundary-Layer Transition 1

12 Approach of Erm amp Joubert (1991) 2

13 Empirical Expressions to Determine Sizes of Tripping Devices 4

2 Preston-Tube Method of Measuring Skin-Friction Coefficients 4

3 Test Program 7

31 Test Facility 7

32 Test Model 7

33 Tripping Devices 10

34 Pressure Scanners 10

35 Data Acquisition Software 12

36 Experimental Procedure 12

37 Data Reduction 13

4 Results 14

41 Skin Friction Without a Tripping Device 14

42 Skin Friction With Tripping Devices 16

421 Comparison of the Different Trip Devices 21

422 Scaling of Skin Friction with Reynolds Number 22

423 Over-stimulation and the Maximum Trip Reynolds Number 23

43 Pressure Coefficients 24

44 Pressure Gradients 26

5 Comparison with CFD Predictions 29

6 Conclusions 30

7 Acknowledgements 32

Appendices

UNCLASSIFIED ix

DSTOndashTRndash2898 UNCLASSIFIED

A Summary of Tripping Devices Used in Previous Experiments 35

B Preston Tube Data Processing 36

C Skin Friction Coefficients 37

D Pressure Coefficients 45

x UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Glossary

DARPA Defense Advanced Research Projects AgencyCERP Corporate Enabling Research ProgramCFD Computational Fluid DynamicsLSWT Low-Speed Wind TunnelDSTO Defence Science and Technology Organisation

Notation

Cf Local skin-friction coefficientCp Pressure coefficientd Outer diameter of Preston tubedT Diameter of trip wireh Height of grit transition strippinfin Free-stream static pressurepp Total pressure of Preston tubeps Model surface static pressurept Free-stream total pressurep+x Non-dimensional pressure gradient parameterRe Reynolds numberRedT Reynolds number based on diameter of wireRex Reynolds number based on the stream-wise coordinateRext Streamwise Reynolds number of transition pointU Streamwise velocity in boundary layerU1 Streamwise velocity at edge of boundary layerUinfin Nominal streamwise velocity in tunnel working-sectionUτ Friction velocityw Width of grit transition stripx Streamwise coordinatext Streamwise coordinate of transition pointy Wall normal coordinate∆p ∆p = pp minus psν Kinematic viscosityρ Fluid densityτ0 Wall shear stress

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DSTOndashTRndash2898 UNCLASSIFIED

THIS PAGE IS INTENTIONALLY BLANK

xii UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

1 Introduction

This work aims to understand flow fields about a submarine As part of this programa series of experiments have been conducted in the Low-Speed Wind Tunnel (LSWT) atthe Defence Science and Technology Organisation (DSTO) to quantify the skin-frictiondistributions on a generic submarine model and in the process investigate the effectivenessof a limited range of tripping devices The results also provide a reference data set forcomputational fluid dynamics (CFD) validation of a submarine model

When conducting tests in wind tunnels on a sub-scale model for results of the exper-iment to be transferable to the full-scale vehicle the flow patterns and load coefficientson the model and the full-size vehicle need to be made similar Ideally this is achievedthrough matching the Reynolds number of the flow over the model to that of the full-scalevehicle However in practice this is difficult to achieve and is not always possible To en-sure that the flow features on the model are representative of those for the full-size vehiclea tripping device can be used such that the boundary layers (ie regions of laminar flowlaminar-to-turbulent transition and turbulent flow) are made similar However differenttripping devices can impart different disturbances into the flow In order to correctly stim-ulate the boundary layer on the submarine model and avoid over- or under-stimulationthe type and size of tripping devices need to be selected for a given Reynolds numberor Reynolds number range and also for a specific trip location Additionally the chosentripping device will be specific to a given tunnel and would be dependent on factors suchas the level of free-stream turbulence in the tunnel

dT

Ud

Trip wire

xd

Laminar Transition Turbulent

Boundary-layeredge

U1

Figure 1 Diagrammatic representation of a boundary layer being tripped based on adiagram given by White (1974)

11 Boundary-Layer Transition

Boundary-layer transition is a complicated physical process dependent on instability mech-anisms including Tollmien-Schlichting waves crossflow and Gortler instabilities (see Reedamp Saric 2008) Over the years there have been numerous articles published on transi-tion both from experimental investigations and CFD analyses in low-speed transonic

UNCLASSIFIED 1

DSTOndashTRndash2898 UNCLASSIFIED

and hypersonic flow regimes (for example Schlatter amp Henningson 2009) Details of thetransition process are still not fully understood In the present report transition physicalprocesses are not considered instead attention is focused on how to stabilise the posi-tion of the transition using a tripping device and to ensure that the turbulent boundarylayer is neither under- or over-stimulated irrespective of the flow physics associated withtransition

12 Approach of Erm amp Joubert (1991)

A diagrammatic representation of a boundary layer being tripped is shown in Figure 1where dT is the height of the tripping device U1 is the streamwise velocity at the edge ofthe boundary layer xd is the location of the tripping device measured from the nose ofthe model and Ud is the velocity in the boundary layer at the top of the device

A question that had to be addressed was what is the best size and type of trippingdevice to use in the current experiments in the LSWT to trip the boundary layer on thesubmarine model Erm amp Joubert (1991) faced a similar question in their studies on low-Reynolds-number flows over a smooth flat surface in a zero pressure gradient For differenttypes of tripping devices they measured longitudinal skin-friction coefficients for a rangeof free-stream velocities Their data for a 12 mm wire tripping device are reproduced inFigure 2 From this figure it can be seen that as the velocity is increased from 8 ms thedevice imparts an increased amount of turbulent energy into the flow so that the laminar-to-turbulent transition region moves upstream They conjectured that correct stimulationis associated with a particular curve when the peaks of successive curves correspondingto higher velocities do not advance significantly upstream Velocities lower than thatcorresponding to the particular curve were obviously associated with under-stimulatedflows since the peaks of the curves were well downstream of the device and thus thedevice was therefore not completely effective in tripping the flow Since the velocitycorresponding to the particular curve establishes a turbulent boundary layer almost to thepossible upstream limit of turbulent flow it seemed reasonable to assume that the maineffect of higher velocities was to overstimulate the flow

The x-coordinate corresponding to the peaks of Figure 2 are plotted in Figure 3 as afunction of streamwise velocity and it is apparent that the above condition for correct stim-ulation was satisfied when the velocity was between 10 and 12 ms This corresponds to aminimum Reynolds number of the tripping device in the range of RedT = U1dT ν = 800to 960 where ν is the kinematic viscosity For the case where a trip device has aReynolds number greater than the minimum required the tripping device may overstim-ulate the flow Note over-stimulation does not necessarily result in higher skin-frictionwhen compared to a correctly stimulated layer Rather it means that the disturbanceintroduced by the tripping device is felt downstream of the transition region and leadsto a ldquonon-standardrdquo turbulent boundary initially developing Ideally to assess whetherover-stimulation has occurred complete velocity profiles in the turbulent region need tobe measured and compared against reference data sets such as those collated by Coles(1962)

It should be noted that in the current work the boundary layer develops in a pressuregradient with wall curvature in both the streamwise and spanwise directions Whereas

2 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

the work of Erm amp Joubert (1991) was undertaken on a flat plate zero pressure gradientthis means the RedT values given above cannot be applied directly to predict the trip sizerequired However the approach taken here broadly follows that of Erm amp Joubert (1991)in that a range of trip Reynolds numbers were tested (by varying both freestream velocityand trip size) and the skin-friction downstream of the trip measured

0 01 02x (m)

03 04 05

Figure 2 Cf vs x measurements for a 12 mm diameter trip wire for different free-streamvelocities as obtained by Erm amp Joubert (1991)

8 9 10 11 12 13 14

xlocation

(m)of

peakCf

Location of peak Cf

Location of trip device

01

02

0

Uinfin (ms)

Figure 3 Location of the peak Cf values shown in Figure 2

UNCLASSIFIED 3

DSTOndashTRndash2898 UNCLASSIFIED

13 Empirical Expressions to Determine Sizes of TrippingDevices

Researchers have proposed different empirical expressions for determining the size of deviceto use to trip the flow The relationships incorporate parameters including the height ofthe tripping device dT the velocity at the edge of the boundary layer U1 the velocity inthe undisturbed boundary layer at the top of the device Ud and the wall friction velocityevaluated at the device Uτ The friction velocity is defined by τ0 = ρU2

τ where τ0 is thesurface shear stress and ρ is the fluid density Recommendations for fully-effective trippingcover quite a wide range Tani et al (1940) proposed the criterion UτdT ν = 13 Fage ampPreston (1941) proposed UτdT ν = 20 Braslow amp Knox (1958) proposed UddT ν = 600and Gibbings (1959) proposed U1dT ν = 826 It should be noted that the criterion ofGibbings (1959) is based on a review of many data sets included those of Tani amp Sato(1956) and Fage amp Preston (1941) Gibbings (1959) expresses the Tani amp Sato (1956)and Fage amp Preston (1941) criteria as Reynolds numbers based on the freestream velocitywhich gives values of U1dT ν = 600 and 840 respectively The criterion given aboverepresent minimum values of the tripping device Reynolds number required to correctlytrip the boundary layer and agree with the results of Erm amp Joubert (1991)

An analysis of the literature for tests done on bodies of revolution indicated that thereis no consistent approach for selecting the size and type of device to use on such bodiesAppendix A gives details of devices used by different investigators for bodies of revolutiontogether with other experimental information Based on the freestream velocity and tripheight the Reynolds numbers of the trip devices given in Appendix A range from 200 to40 times 103 For the present investigation the approach used to establish the effects thatdifferent devices had on tripping laminar boundary layers was similar to that used byErm amp Joubert (1991) for a smooth flat plate in a zero pressure gradient Using theirtechnique it is possible to establish the size and type of tripping device to be used for agiven velocity to obtain correctly stimulated turbulent boundary layers

2 Preston-Tube Method of Measuring

Skin-Friction Coefficients

Skin-friction coefficients in a turbulent boundary layer flowing over a smooth surface canbe measured in a number of different ways (Fernholz et al 1996) including using Prestontubes (Preston 1954) from velocity profiles and using devices mounted flush with thesurface of a model Of the alternative approaches the Preston-tube method is convenientand is widely used The method makes use of a simple Pitot tube placed on the surfaceof a body and when used this way it is termed a Preston tube The method depends onan underlining assumption that in the region adjacent to the surface the flow is primarilydetermined by the surface shear stress and the properties of the fluid and is independentof factors such as pressure gradient and surface curvature The assumption implies thatthe velocity profile in a turbulent boundary layer adjacent to the surface is given by

U

Uτ= f

(Uτy

ν

)(1)

4 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

where U is the local stream-wise velocity Uτ is the friction velocity f is a universalfunction y is the wall normal coordinate and ν is the kinematic viscosity Equation (1) isoften referred to as the ldquolaw of the wallrdquo (Coles 1956)

A Pitot tube placed on the wall will measure a pressure relative to the wall staticpressure of ∆p = ρU22 at an effective coordinate y = c0d where d is the outer diameterof the Pitot tube and c0 is an unknown constant Substituting the values U =

radic(2∆pρ)

and y = cod into (1) yields a relationship between the wall shear stress fluid propertiesPreston-tube pressure difference and the tube diameter which is given by

2∆p

ρUτ2 =

[f

(Uτ c0d

ν

)]2 (2)

Alternatively for the purpose of measuring skin friction (2) can be expressed more con-veniently in the form

τ0d2

4ρν2= F

(∆pd2

4ρν2

)(3)

where c0 has been absorbed into the function F The function F represents the ldquocalibra-tionrdquo function for a Preston tube and several experimentally derived forms exist in theliterature (see Preston 1954 Patel 1965 Zagarola et al 2001) Generally the calibrationis determined by placing the Preston tube in a pipe flow where the wall shear stress (orfriction factor) can be determined accurately by measuring the pressure gradient in thepipe

For the data presented in this report the calibration of Patel (1965) was used todetermine the wall shear stress The calibration curve of Patel (1965) is given as follows

xlowast =ylowast + 2 log10(195ylowast + 410) for 55 ltUτd

2νlt 800 (4)

ylowast =08287 minus 01381xlowast + 01437xlowast2 minus 0006xlowast3 for 56 ltUτd

2νlt 55 and (5)

ylowast =1

2xlowast + 0037 for

Uτd

2νlt 56 (6)

where

xlowast = log10

(∆pd2

4ρν2

)and ylowast = log10

(τ0d

2

4ρν2

)

The local skin friction coefficient Cf is then found using

Cf =τ0

12ρU

21

(7)

where U1 is the streamwise velocity at the edge of the boundary layer

The calibration given by (4)-(6) is valid only for a hydrodynamically smooth surfaceA surface is considered hydrodynamically smooth provided that the height of surfaceroughness elements remain less than 5νUτ (Jimenez 2004) The minimum value of 5νUτthat was measured was approximately 4microm and the measured surface finish was found tobe an order of magnitude less than this value (Section 32) Hence the requirement of ahydrodynamically smooth surface is satisfied for this experiment

UNCLASSIFIED 5

DSTOndashTRndash2898 UNCLASSIFIED

The fundamental requirement for using a Preston tube is that the boundary layer isin a turbulent state and that the dimension of the Preston tube is such that it remainswithin the region where (1) is valid (ie from (4) Uτdν lt 1600) The diameter of thePreston tube for all experiments was d = 06 mm and this ensured that Uτdν remainedless than 1600 well within the range of the calibration (4)

It is known that for sufficiently strong pressure gradients the form of (1) changes (seeNickels 2004) Patel (1965) quantifies the effect of pressure gradients using the non-dimensional pressure gradient parameter1

p+x =ν

ρU3τ

dp

dx (8)

The error associated with using a Preston tube in pressure gradients is quantified by Patel(1965) and is given by the following inequalities

1 Adverse pressure gradient

Max Error 3 0 lt p+x lt 001 andUτd

νle 200 (9a)

Max Error 6 0 lt p+x lt 0015 andUτd

νle 250 (9b)

2 Favourable pressure gradient

Max Error 3 minus0005 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10a)

Max Error 6 minus0007 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10b)

The pressure gradient data are presented in Section 44 and were found to fall within thelimits of (9a) and (10a) indicating that the skin-friction coefficients are valid to withinplusmn3 This accuracy is similar to the alternative direct skin-friction measuring techniqueswhich typically achieve an accuracy of plusmn4 (Fernholz et al 1996)

The effect of model spanwise curvature on (4)-(6) is not quantified A reasonableassumption is that since the boundary layer thickness is much less than the model diameterthe effect of spanwise model curvature can be neglected

The Preston-tube method as outlined above requires that the boundary layer is in aturbulent state For this reason the method cannot be used to infer the skin friction atlocations were the boundary layer is in a laminar state However the ∆p values read by thePreston tube can be used to determine where laminar-to-turbulent transition occurs Theregion of transition is associated with a discontinuity in ∆p when plotted as a functionof streamwise coordinate x as shown by Erm amp Joubert (1991)

1for clarity we have adopted the notation for the pressure gradient parameter used by Nickels (2004)Patel (1965) uses the symbol ∆

6 UNCLASSIFIED

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Figure 4 LSWT Layout see Erm (2003)

3 Test Program

In this preliminary investigation four different tripping devices were used to investigatethe effect of the device on the skin-friction profile of a generic sub-scale submarine modelTests were conducted both with and without the tripping devices at a range of nominalfree-stream velocities Uinfin ranging from Uinfin = 40 to 70 ms to assess their effectivenessin tripping the boundary layer

31 Test Facility

The Low-Speed Wind Tunnel at DSTO is a closed circuit continuous flow tunnel with acontraction ratio of 41 The test section has an irregular octagonal shape with a heightof 213 m a width of 274 m and a length of 6553 m with a longitudinal turbulenceintensity of approximately 04 in the region where the models are tested (see Erm2003) An outline of the plan of the wind tunnel is shown in Figure 4 Free-streamvelocities were measured using static pressure rings at the upstream and downstreamends of the contraction A Pitot-static probe mounted on the side wall near the front ofthe working section was used to provide an independent measurement of the free-streamvelocity

32 Test Model

The sub-scale submarine model utilised in these tests is referred to as the Joubert modelsince the geometry is based on the work of Joubert (2004) and Joubert (2006) as well asLoid amp Bystrom (1983) The model was designed for the purpose of experimental and

UNCLASSIFIED 7

DSTOndashTRndash2898 UNCLASSIFIED

1

2 345

6 7 8 91011

12 13 141516

17 181920

212223

24 252627

28 29 303132

33 34

35

Top view

Side view

Figure 5 Schematic of scale model showing static-pressure port locations green and redmarkers represent the starboard and port static-pressure ports respectively

numerical studies and has no full-scale equivalent While the full model includes a casingcentre fin and control surfaces all tests reported here were conducted on the axisymmetricbody shape only

The model was machined from aluminum and consists of an ellipsoidal nose a cylin-drical centre-body and a streamlined tail section At the design stage an N6 surface finishwas specified for the model which corresponds to a roughness of 08microm in waviness Af-ter manufacture the surface finish was checked using a Surface Roughness Indicator andthe finish was found to be better than the design specification The model was anodisedwhich increased the thickness of the natural oxide layer by about 10microm

The model is 1350 mm long with a maximum diameter of 185 mm and slendernessratio of 73 where the slenderness ratio is defined as hull length divided by maximumhull diameter The model contains 21 longitudinal static-pressure ports on the centre-lineof the upper surface and 14 lateral static-pressure ports offset to the port and starboardsides of the upper surface centre-line Figure 5 shows the stream-wise location of thestatic-pressure ports

The model was supported by a single pylon as shown in Figure 6 All tests were carriedout at zero angle of yaw and zero angle of pitch The origin of the body coordinate systemis located at the nose of the submarine model The x-axis corresponds to the axis ofsymmetry of the model

8 UNCLASSIFIED

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Figure 6 Submarine model mounted in LSWT showing pylon support and pitch controlarm

UNCLASSIFIED 9

DSTOndashTRndash2898 UNCLASSIFIED

Table 1 Details of tripping devices where the Reynolds number is based on the height ofthe device The minimum Reynolds number and maximum Reynolds number correspondto nominal freestream velocities of Uinfin = 40 ms and Uinfin = 70 ms respectively where his the height of the grit and w is the width of the grit

Device Dimensions (mm) RedT (min) RedT (max)

Wire 1 dT = 01 281 496Wire 2 dT = 02 577 1015Wire 3 dT = 05 1443 256680 Grit h = 021 w = 3 605 1073

33 Tripping Devices

In this work four tripping devices were tested and consisted of circular wires with diame-ters dT = 01 02 and 05 mm as well as a distributed silicon carbide grit of size 80 havinga width of 3 mm The circular wires were bent to conform to the local diameter of thesubmarine and then attached with ldquosuper-gluerdquo such that there was no gap between thewire and the model surface Figure 7 The silicon carbide grit is prepared by distributinga layer of grit on double-sided sticky tape the tape is then adhered to the submarineFigure 8 The tripping devices were attached to the submarine model circumferentiallylocated at a streamwise coordinate of x = 675 mm measured from the nose of the sub-marine which corresponds to 5 of the total model length The dimensions of the tripdevices along with the Reynolds number range of the trip devices are summarised inTable 1 Note that the Reynolds number of the trip device is defined as RedT = U1dT νwhere for the case of the 80 grit dT is replaced by the grit height h

34 Pressure Scanners

Pressure Systems Incorporated (PSI) brand pressure scanners were used to measure allstatic and total pressures The pressure scanners are differential pressure measurementunits consisting of an array of silicon piezoresistive pressure sensors one for each pressureport The outputs of the sensors are electronically multiplexed through a single on-boardinstrumentation amplifier using binary addressing The scanners include a two-positioncalibration manifold actuated by momentary pulses of control pressures In the calibrateposition all sensors are connected to a common calibration pressure port A series ofaccurately-measured pressures is applied through this port to characterize the sensorsProper and periodic on-line calibration maintains static errors within plusmn003 or betterof the full-scale pressure range

The pressure scanners are controlled and sampled using a PSI 8400 electronic measure-ment system It is a modular parallel processing system for high-speed pressure scanningat up to 20000 measurements per second and allows the use of digitally temperaturecompensated pressure scanners

Two differential pressure scanners were used in the experiments All pressures aremeasured relative to the free-stream static pressure pinfin as measured by the referencefree-stream Pitot-static probe Each pressure scanner contained 32 ports The full-scale

10 UNCLASSIFIED

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Figure 7 Location of trip wire

Figure 8 Photo showing the 3 mm wide band of 80 grit transition strip

UNCLASSIFIED 11

DSTOndashTRndash2898 UNCLASSIFIED

pressure range of the scanners is 249 kPa (ldquo10 inches-of-water scannerrdquo) and 689 kPa(ldquo1 psi scannerrdquo) The 689 kPa scanner was used to read the static pressure at the longi-tudinal ports as well as the output from the Preston tube and the Pitot-static probe

For the purpose of cross-checking and for redundancy the Preston tube was connectedto two independent ports of the 689 kPa scanner and the two readings averaged For thisscanner pressures could be read to an accuracy of 6890 times 00003 Pa ie about 2 Pa Theminimum ∆p measured by the Preston tube was 145 Pa which gives a pressure scannerresolution of 14 However this minimum ∆p was recorded for a location where thePreston tube was in a laminar boundary layer and such data is only useful in a qualitativesense (see Section 2) For locations were the boundary layer is turbulent the minimum ∆pwas 340 Pa which gives a pressure scanner resolution of 06 The 249 kPa scanner wasused mainly to acquire the static pressures at the lateral ports

35 Data Acquisition Software

A software package called ImPressOne was used which communicates with the PSI 8400and displays and acquires the pressure data for the model under test For the staticpressure measurements 100 readings were acquired at each pressure port at a samplingrate of 20 Hz For the Preston-tube measurements the sample rate was increased and100 samples were acquired at each pressure port at a sampling rate of 50 Hz for eachfree-stream velocity

36 Experimental Procedure

The hull was tested with each of the selected tripping devices listed in Table 1 as wellas without a tripping device resulting in five different test configurations For each testconfiguration the static pressures were initially acquired for that particular configurationfollowed by the Preston-tube measurements

A Preston tube having a diameter of 06 mm was attached to the surface of the modelusing both plasticine and tape to ensure that the tube was positioned as flat as possibleon the surface of the model as shown in Figure 9 Preston-tube measurement were takenon the upper surface of the submarine model along a line directly above the centre-lineof the model For the dT = 02 and 05 mm wires and the grit case measurements weretaken from x = 73 mm to x = 1065 mm for a total of 18 stations For the dT = 01 mmwire measurements were limited to 3 stations between x = 305 mm and x = 442 mmThe stream-wise coordinates for the Preston tube measurements are given in the Table 2Data were acquired for a range of free-stream velocities from 40 to 70 ms in incrementsof 5 ms

For each nominal velocity the corresponding model Reynolds number was calcu-lated assuming standard temperature and atmospheric pressure conditions 20C and101 325 Pa respectively For each given test the temperature and static pressure of theair within the test section were logged and the air density and viscosity were calculatedTo account for daily variations in temperature and atmospheric pressure the freestream

12 UNCLASSIFIED

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Flow direction

Figure 9 Preston tube located on the centre-line of the upper-surface of submarine

velocity was adjusted to ensure that the model Reynolds number remained constant foreach given nominal velocity condition as shown in Table 3

Table 2 Skin-friction measurement stations Where applicable the corresponding staticport number is given For the dT = 01 mm wire measurements were only taken at stations3050 3600 as well as an additional station at x = 4425 mm

xmm 731 787 843 900 1125 1350 1575 1800 2150Static port - - - 6 - 7 - 8 -

xmm 2500 3050 3600 5250 7000 8700 9500 10100 10650Static port 9 - 12 13 14 17 18 21 24

Table 3 Reynolds numbers (based on submarine length 135 m) corresponding to thenominal free-stream velocities

Nominal Uinfin 40 45 50 55 60 65 70 msRe 358 403 448 493 537 582 627 times106

37 Data Reduction

The static pressure readings from the pressure ports were converted to pressure coefficientsusing the relationship

Cp =ps minus pinfinpt minus pinfin

(11)

where pinfin is the reference free-stream static pressure pt is the reference free-stream totalpressure and ps is the static pressure on the surface of the submarine model

As explained in Section 34 all Preston tube pressures are measured relative to the free-stream static pressure In order to apply the Preston tube calibration (4)-(6) the loggedPreston-tube pressure differences (ie pp minus pinfin) must first be converted to a ∆p = pp minus ps

UNCLASSIFIED 13

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 6: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

Lincoln ErmAerospace Division

Lincoln Erm obtained a Bachelor of Engineering (Mechanical)degree in 1967 and a Master of Engineering Science degree in1969 both from the University of Melbourne His Masterrsquos de-gree was concerned with the yielding of aluminium alloy whensubjected to both tensile and torsional loading He joined theAeronautical Research Laboratories (now called the DefenceScience and Technology Organisation) in 1970 and has workedon a wide range of research projects including the prediction ofthe performance of gas-turbine engines under conditions of pul-sating flow parametric studies of ramrocket performance flowinstability in aircraft intakes and problems associated with thelanding of a helicopter on the flight deck of a ship Concurrentlywith some of the above work he studied at the University ofMelbourne and in 1988 obtained his Doctor of Philosophy de-gree for work on low-Reynolds-number turbulent boundary lay-ers Since this time he has undertaken research investigationsin the low-speed wind tunnel and the water tunnel Recentwork has been concerned with extending the testing capabili-ties of the water tunnel including developing a two-componentstrain-gauge-balance load-measurement system for the tunneland developing a dynamic-testing capability for the tunnel en-abling aerodynamic derivatives to be measured on models

Aliya ValiyffAerospace Division

Aliya Valiyff graduated from the University of Adelaide in 2009with a Bachelor of Aerospace Engineering and Bachelor of Sci-ence (Applied Mathematics and Physics) with 1st class honoursShe commenced work with DSTO in 2010 and during her timeshe has mainly worked within the Unmanned Aerial System -Corporate Enabling Research Programme (CERP) undertak-ing research on flapping wing and the flight and the UnderseaWarfare- CERP

vi UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Simon HenbestAerospace Division

Simon Henbest obtained a Bachelor of Engineering (Mechan-ical) degree with honours in 1977 and a PhD in 1983 bothfrom The University of Melbourne His PhD titled rdquoThe Struc-ture of Turbulent Pipe Flowrdquo provide experimental support toTownsendrsquos attached eddy hypothesis for wall bounded flowsIn 1984 he was awarded an Australian National Research Fel-lowship and continued wall turbulence research at the Univer-sity of Melbourne In 1987 he commenced employment at theAeronautical Research Laboratories (now called the DefenceScience and Technology Organisation) and obtained merit pro-motions to both Senior Research Scientist and Principal Re-search Scientist While at DSTO he has been involved in re-search into high speed jet and aeroacoustic cavity flows the IRsignature prediction of aircraft numerous aerodynamic testingprogrammes He has acted as a Research Leader for extendedperiods in AVD AOD and HPPD He is currently Head of FluidMechanics in Aerospace Division

UNCLASSIFIED vii

DSTOndashTRndash2898 UNCLASSIFIED

THIS PAGE IS INTENTIONALLY BLANK

viii UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Contents

Glossary xi

Notation xi

1 Introduction 1

11 Boundary-Layer Transition 1

12 Approach of Erm amp Joubert (1991) 2

13 Empirical Expressions to Determine Sizes of Tripping Devices 4

2 Preston-Tube Method of Measuring Skin-Friction Coefficients 4

3 Test Program 7

31 Test Facility 7

32 Test Model 7

33 Tripping Devices 10

34 Pressure Scanners 10

35 Data Acquisition Software 12

36 Experimental Procedure 12

37 Data Reduction 13

4 Results 14

41 Skin Friction Without a Tripping Device 14

42 Skin Friction With Tripping Devices 16

421 Comparison of the Different Trip Devices 21

422 Scaling of Skin Friction with Reynolds Number 22

423 Over-stimulation and the Maximum Trip Reynolds Number 23

43 Pressure Coefficients 24

44 Pressure Gradients 26

5 Comparison with CFD Predictions 29

6 Conclusions 30

7 Acknowledgements 32

Appendices

UNCLASSIFIED ix

DSTOndashTRndash2898 UNCLASSIFIED

A Summary of Tripping Devices Used in Previous Experiments 35

B Preston Tube Data Processing 36

C Skin Friction Coefficients 37

D Pressure Coefficients 45

x UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Glossary

DARPA Defense Advanced Research Projects AgencyCERP Corporate Enabling Research ProgramCFD Computational Fluid DynamicsLSWT Low-Speed Wind TunnelDSTO Defence Science and Technology Organisation

Notation

Cf Local skin-friction coefficientCp Pressure coefficientd Outer diameter of Preston tubedT Diameter of trip wireh Height of grit transition strippinfin Free-stream static pressurepp Total pressure of Preston tubeps Model surface static pressurept Free-stream total pressurep+x Non-dimensional pressure gradient parameterRe Reynolds numberRedT Reynolds number based on diameter of wireRex Reynolds number based on the stream-wise coordinateRext Streamwise Reynolds number of transition pointU Streamwise velocity in boundary layerU1 Streamwise velocity at edge of boundary layerUinfin Nominal streamwise velocity in tunnel working-sectionUτ Friction velocityw Width of grit transition stripx Streamwise coordinatext Streamwise coordinate of transition pointy Wall normal coordinate∆p ∆p = pp minus psν Kinematic viscosityρ Fluid densityτ0 Wall shear stress

UNCLASSIFIED xi

DSTOndashTRndash2898 UNCLASSIFIED

THIS PAGE IS INTENTIONALLY BLANK

xii UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

1 Introduction

This work aims to understand flow fields about a submarine As part of this programa series of experiments have been conducted in the Low-Speed Wind Tunnel (LSWT) atthe Defence Science and Technology Organisation (DSTO) to quantify the skin-frictiondistributions on a generic submarine model and in the process investigate the effectivenessof a limited range of tripping devices The results also provide a reference data set forcomputational fluid dynamics (CFD) validation of a submarine model

When conducting tests in wind tunnels on a sub-scale model for results of the exper-iment to be transferable to the full-scale vehicle the flow patterns and load coefficientson the model and the full-size vehicle need to be made similar Ideally this is achievedthrough matching the Reynolds number of the flow over the model to that of the full-scalevehicle However in practice this is difficult to achieve and is not always possible To en-sure that the flow features on the model are representative of those for the full-size vehiclea tripping device can be used such that the boundary layers (ie regions of laminar flowlaminar-to-turbulent transition and turbulent flow) are made similar However differenttripping devices can impart different disturbances into the flow In order to correctly stim-ulate the boundary layer on the submarine model and avoid over- or under-stimulationthe type and size of tripping devices need to be selected for a given Reynolds numberor Reynolds number range and also for a specific trip location Additionally the chosentripping device will be specific to a given tunnel and would be dependent on factors suchas the level of free-stream turbulence in the tunnel

dT

Ud

Trip wire

xd

Laminar Transition Turbulent

Boundary-layeredge

U1

Figure 1 Diagrammatic representation of a boundary layer being tripped based on adiagram given by White (1974)

11 Boundary-Layer Transition

Boundary-layer transition is a complicated physical process dependent on instability mech-anisms including Tollmien-Schlichting waves crossflow and Gortler instabilities (see Reedamp Saric 2008) Over the years there have been numerous articles published on transi-tion both from experimental investigations and CFD analyses in low-speed transonic

UNCLASSIFIED 1

DSTOndashTRndash2898 UNCLASSIFIED

and hypersonic flow regimes (for example Schlatter amp Henningson 2009) Details of thetransition process are still not fully understood In the present report transition physicalprocesses are not considered instead attention is focused on how to stabilise the posi-tion of the transition using a tripping device and to ensure that the turbulent boundarylayer is neither under- or over-stimulated irrespective of the flow physics associated withtransition

12 Approach of Erm amp Joubert (1991)

A diagrammatic representation of a boundary layer being tripped is shown in Figure 1where dT is the height of the tripping device U1 is the streamwise velocity at the edge ofthe boundary layer xd is the location of the tripping device measured from the nose ofthe model and Ud is the velocity in the boundary layer at the top of the device

A question that had to be addressed was what is the best size and type of trippingdevice to use in the current experiments in the LSWT to trip the boundary layer on thesubmarine model Erm amp Joubert (1991) faced a similar question in their studies on low-Reynolds-number flows over a smooth flat surface in a zero pressure gradient For differenttypes of tripping devices they measured longitudinal skin-friction coefficients for a rangeof free-stream velocities Their data for a 12 mm wire tripping device are reproduced inFigure 2 From this figure it can be seen that as the velocity is increased from 8 ms thedevice imparts an increased amount of turbulent energy into the flow so that the laminar-to-turbulent transition region moves upstream They conjectured that correct stimulationis associated with a particular curve when the peaks of successive curves correspondingto higher velocities do not advance significantly upstream Velocities lower than thatcorresponding to the particular curve were obviously associated with under-stimulatedflows since the peaks of the curves were well downstream of the device and thus thedevice was therefore not completely effective in tripping the flow Since the velocitycorresponding to the particular curve establishes a turbulent boundary layer almost to thepossible upstream limit of turbulent flow it seemed reasonable to assume that the maineffect of higher velocities was to overstimulate the flow

The x-coordinate corresponding to the peaks of Figure 2 are plotted in Figure 3 as afunction of streamwise velocity and it is apparent that the above condition for correct stim-ulation was satisfied when the velocity was between 10 and 12 ms This corresponds to aminimum Reynolds number of the tripping device in the range of RedT = U1dT ν = 800to 960 where ν is the kinematic viscosity For the case where a trip device has aReynolds number greater than the minimum required the tripping device may overstim-ulate the flow Note over-stimulation does not necessarily result in higher skin-frictionwhen compared to a correctly stimulated layer Rather it means that the disturbanceintroduced by the tripping device is felt downstream of the transition region and leadsto a ldquonon-standardrdquo turbulent boundary initially developing Ideally to assess whetherover-stimulation has occurred complete velocity profiles in the turbulent region need tobe measured and compared against reference data sets such as those collated by Coles(1962)

It should be noted that in the current work the boundary layer develops in a pressuregradient with wall curvature in both the streamwise and spanwise directions Whereas

2 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

the work of Erm amp Joubert (1991) was undertaken on a flat plate zero pressure gradientthis means the RedT values given above cannot be applied directly to predict the trip sizerequired However the approach taken here broadly follows that of Erm amp Joubert (1991)in that a range of trip Reynolds numbers were tested (by varying both freestream velocityand trip size) and the skin-friction downstream of the trip measured

0 01 02x (m)

03 04 05

Figure 2 Cf vs x measurements for a 12 mm diameter trip wire for different free-streamvelocities as obtained by Erm amp Joubert (1991)

8 9 10 11 12 13 14

xlocation

(m)of

peakCf

Location of peak Cf

Location of trip device

01

02

0

Uinfin (ms)

Figure 3 Location of the peak Cf values shown in Figure 2

UNCLASSIFIED 3

DSTOndashTRndash2898 UNCLASSIFIED

13 Empirical Expressions to Determine Sizes of TrippingDevices

Researchers have proposed different empirical expressions for determining the size of deviceto use to trip the flow The relationships incorporate parameters including the height ofthe tripping device dT the velocity at the edge of the boundary layer U1 the velocity inthe undisturbed boundary layer at the top of the device Ud and the wall friction velocityevaluated at the device Uτ The friction velocity is defined by τ0 = ρU2

τ where τ0 is thesurface shear stress and ρ is the fluid density Recommendations for fully-effective trippingcover quite a wide range Tani et al (1940) proposed the criterion UτdT ν = 13 Fage ampPreston (1941) proposed UτdT ν = 20 Braslow amp Knox (1958) proposed UddT ν = 600and Gibbings (1959) proposed U1dT ν = 826 It should be noted that the criterion ofGibbings (1959) is based on a review of many data sets included those of Tani amp Sato(1956) and Fage amp Preston (1941) Gibbings (1959) expresses the Tani amp Sato (1956)and Fage amp Preston (1941) criteria as Reynolds numbers based on the freestream velocitywhich gives values of U1dT ν = 600 and 840 respectively The criterion given aboverepresent minimum values of the tripping device Reynolds number required to correctlytrip the boundary layer and agree with the results of Erm amp Joubert (1991)

An analysis of the literature for tests done on bodies of revolution indicated that thereis no consistent approach for selecting the size and type of device to use on such bodiesAppendix A gives details of devices used by different investigators for bodies of revolutiontogether with other experimental information Based on the freestream velocity and tripheight the Reynolds numbers of the trip devices given in Appendix A range from 200 to40 times 103 For the present investigation the approach used to establish the effects thatdifferent devices had on tripping laminar boundary layers was similar to that used byErm amp Joubert (1991) for a smooth flat plate in a zero pressure gradient Using theirtechnique it is possible to establish the size and type of tripping device to be used for agiven velocity to obtain correctly stimulated turbulent boundary layers

2 Preston-Tube Method of Measuring

Skin-Friction Coefficients

Skin-friction coefficients in a turbulent boundary layer flowing over a smooth surface canbe measured in a number of different ways (Fernholz et al 1996) including using Prestontubes (Preston 1954) from velocity profiles and using devices mounted flush with thesurface of a model Of the alternative approaches the Preston-tube method is convenientand is widely used The method makes use of a simple Pitot tube placed on the surfaceof a body and when used this way it is termed a Preston tube The method depends onan underlining assumption that in the region adjacent to the surface the flow is primarilydetermined by the surface shear stress and the properties of the fluid and is independentof factors such as pressure gradient and surface curvature The assumption implies thatthe velocity profile in a turbulent boundary layer adjacent to the surface is given by

U

Uτ= f

(Uτy

ν

)(1)

4 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

where U is the local stream-wise velocity Uτ is the friction velocity f is a universalfunction y is the wall normal coordinate and ν is the kinematic viscosity Equation (1) isoften referred to as the ldquolaw of the wallrdquo (Coles 1956)

A Pitot tube placed on the wall will measure a pressure relative to the wall staticpressure of ∆p = ρU22 at an effective coordinate y = c0d where d is the outer diameterof the Pitot tube and c0 is an unknown constant Substituting the values U =

radic(2∆pρ)

and y = cod into (1) yields a relationship between the wall shear stress fluid propertiesPreston-tube pressure difference and the tube diameter which is given by

2∆p

ρUτ2 =

[f

(Uτ c0d

ν

)]2 (2)

Alternatively for the purpose of measuring skin friction (2) can be expressed more con-veniently in the form

τ0d2

4ρν2= F

(∆pd2

4ρν2

)(3)

where c0 has been absorbed into the function F The function F represents the ldquocalibra-tionrdquo function for a Preston tube and several experimentally derived forms exist in theliterature (see Preston 1954 Patel 1965 Zagarola et al 2001) Generally the calibrationis determined by placing the Preston tube in a pipe flow where the wall shear stress (orfriction factor) can be determined accurately by measuring the pressure gradient in thepipe

For the data presented in this report the calibration of Patel (1965) was used todetermine the wall shear stress The calibration curve of Patel (1965) is given as follows

xlowast =ylowast + 2 log10(195ylowast + 410) for 55 ltUτd

2νlt 800 (4)

ylowast =08287 minus 01381xlowast + 01437xlowast2 minus 0006xlowast3 for 56 ltUτd

2νlt 55 and (5)

ylowast =1

2xlowast + 0037 for

Uτd

2νlt 56 (6)

where

xlowast = log10

(∆pd2

4ρν2

)and ylowast = log10

(τ0d

2

4ρν2

)

The local skin friction coefficient Cf is then found using

Cf =τ0

12ρU

21

(7)

where U1 is the streamwise velocity at the edge of the boundary layer

The calibration given by (4)-(6) is valid only for a hydrodynamically smooth surfaceA surface is considered hydrodynamically smooth provided that the height of surfaceroughness elements remain less than 5νUτ (Jimenez 2004) The minimum value of 5νUτthat was measured was approximately 4microm and the measured surface finish was found tobe an order of magnitude less than this value (Section 32) Hence the requirement of ahydrodynamically smooth surface is satisfied for this experiment

UNCLASSIFIED 5

DSTOndashTRndash2898 UNCLASSIFIED

The fundamental requirement for using a Preston tube is that the boundary layer isin a turbulent state and that the dimension of the Preston tube is such that it remainswithin the region where (1) is valid (ie from (4) Uτdν lt 1600) The diameter of thePreston tube for all experiments was d = 06 mm and this ensured that Uτdν remainedless than 1600 well within the range of the calibration (4)

It is known that for sufficiently strong pressure gradients the form of (1) changes (seeNickels 2004) Patel (1965) quantifies the effect of pressure gradients using the non-dimensional pressure gradient parameter1

p+x =ν

ρU3τ

dp

dx (8)

The error associated with using a Preston tube in pressure gradients is quantified by Patel(1965) and is given by the following inequalities

1 Adverse pressure gradient

Max Error 3 0 lt p+x lt 001 andUτd

νle 200 (9a)

Max Error 6 0 lt p+x lt 0015 andUτd

νle 250 (9b)

2 Favourable pressure gradient

Max Error 3 minus0005 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10a)

Max Error 6 minus0007 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10b)

The pressure gradient data are presented in Section 44 and were found to fall within thelimits of (9a) and (10a) indicating that the skin-friction coefficients are valid to withinplusmn3 This accuracy is similar to the alternative direct skin-friction measuring techniqueswhich typically achieve an accuracy of plusmn4 (Fernholz et al 1996)

The effect of model spanwise curvature on (4)-(6) is not quantified A reasonableassumption is that since the boundary layer thickness is much less than the model diameterthe effect of spanwise model curvature can be neglected

The Preston-tube method as outlined above requires that the boundary layer is in aturbulent state For this reason the method cannot be used to infer the skin friction atlocations were the boundary layer is in a laminar state However the ∆p values read by thePreston tube can be used to determine where laminar-to-turbulent transition occurs Theregion of transition is associated with a discontinuity in ∆p when plotted as a functionof streamwise coordinate x as shown by Erm amp Joubert (1991)

1for clarity we have adopted the notation for the pressure gradient parameter used by Nickels (2004)Patel (1965) uses the symbol ∆

6 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 4 LSWT Layout see Erm (2003)

3 Test Program

In this preliminary investigation four different tripping devices were used to investigatethe effect of the device on the skin-friction profile of a generic sub-scale submarine modelTests were conducted both with and without the tripping devices at a range of nominalfree-stream velocities Uinfin ranging from Uinfin = 40 to 70 ms to assess their effectivenessin tripping the boundary layer

31 Test Facility

The Low-Speed Wind Tunnel at DSTO is a closed circuit continuous flow tunnel with acontraction ratio of 41 The test section has an irregular octagonal shape with a heightof 213 m a width of 274 m and a length of 6553 m with a longitudinal turbulenceintensity of approximately 04 in the region where the models are tested (see Erm2003) An outline of the plan of the wind tunnel is shown in Figure 4 Free-streamvelocities were measured using static pressure rings at the upstream and downstreamends of the contraction A Pitot-static probe mounted on the side wall near the front ofthe working section was used to provide an independent measurement of the free-streamvelocity

32 Test Model

The sub-scale submarine model utilised in these tests is referred to as the Joubert modelsince the geometry is based on the work of Joubert (2004) and Joubert (2006) as well asLoid amp Bystrom (1983) The model was designed for the purpose of experimental and

UNCLASSIFIED 7

DSTOndashTRndash2898 UNCLASSIFIED

1

2 345

6 7 8 91011

12 13 141516

17 181920

212223

24 252627

28 29 303132

33 34

35

Top view

Side view

Figure 5 Schematic of scale model showing static-pressure port locations green and redmarkers represent the starboard and port static-pressure ports respectively

numerical studies and has no full-scale equivalent While the full model includes a casingcentre fin and control surfaces all tests reported here were conducted on the axisymmetricbody shape only

The model was machined from aluminum and consists of an ellipsoidal nose a cylin-drical centre-body and a streamlined tail section At the design stage an N6 surface finishwas specified for the model which corresponds to a roughness of 08microm in waviness Af-ter manufacture the surface finish was checked using a Surface Roughness Indicator andthe finish was found to be better than the design specification The model was anodisedwhich increased the thickness of the natural oxide layer by about 10microm

The model is 1350 mm long with a maximum diameter of 185 mm and slendernessratio of 73 where the slenderness ratio is defined as hull length divided by maximumhull diameter The model contains 21 longitudinal static-pressure ports on the centre-lineof the upper surface and 14 lateral static-pressure ports offset to the port and starboardsides of the upper surface centre-line Figure 5 shows the stream-wise location of thestatic-pressure ports

The model was supported by a single pylon as shown in Figure 6 All tests were carriedout at zero angle of yaw and zero angle of pitch The origin of the body coordinate systemis located at the nose of the submarine model The x-axis corresponds to the axis ofsymmetry of the model

8 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 6 Submarine model mounted in LSWT showing pylon support and pitch controlarm

UNCLASSIFIED 9

DSTOndashTRndash2898 UNCLASSIFIED

Table 1 Details of tripping devices where the Reynolds number is based on the height ofthe device The minimum Reynolds number and maximum Reynolds number correspondto nominal freestream velocities of Uinfin = 40 ms and Uinfin = 70 ms respectively where his the height of the grit and w is the width of the grit

Device Dimensions (mm) RedT (min) RedT (max)

Wire 1 dT = 01 281 496Wire 2 dT = 02 577 1015Wire 3 dT = 05 1443 256680 Grit h = 021 w = 3 605 1073

33 Tripping Devices

In this work four tripping devices were tested and consisted of circular wires with diame-ters dT = 01 02 and 05 mm as well as a distributed silicon carbide grit of size 80 havinga width of 3 mm The circular wires were bent to conform to the local diameter of thesubmarine and then attached with ldquosuper-gluerdquo such that there was no gap between thewire and the model surface Figure 7 The silicon carbide grit is prepared by distributinga layer of grit on double-sided sticky tape the tape is then adhered to the submarineFigure 8 The tripping devices were attached to the submarine model circumferentiallylocated at a streamwise coordinate of x = 675 mm measured from the nose of the sub-marine which corresponds to 5 of the total model length The dimensions of the tripdevices along with the Reynolds number range of the trip devices are summarised inTable 1 Note that the Reynolds number of the trip device is defined as RedT = U1dT νwhere for the case of the 80 grit dT is replaced by the grit height h

34 Pressure Scanners

Pressure Systems Incorporated (PSI) brand pressure scanners were used to measure allstatic and total pressures The pressure scanners are differential pressure measurementunits consisting of an array of silicon piezoresistive pressure sensors one for each pressureport The outputs of the sensors are electronically multiplexed through a single on-boardinstrumentation amplifier using binary addressing The scanners include a two-positioncalibration manifold actuated by momentary pulses of control pressures In the calibrateposition all sensors are connected to a common calibration pressure port A series ofaccurately-measured pressures is applied through this port to characterize the sensorsProper and periodic on-line calibration maintains static errors within plusmn003 or betterof the full-scale pressure range

The pressure scanners are controlled and sampled using a PSI 8400 electronic measure-ment system It is a modular parallel processing system for high-speed pressure scanningat up to 20000 measurements per second and allows the use of digitally temperaturecompensated pressure scanners

Two differential pressure scanners were used in the experiments All pressures aremeasured relative to the free-stream static pressure pinfin as measured by the referencefree-stream Pitot-static probe Each pressure scanner contained 32 ports The full-scale

10 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 7 Location of trip wire

Figure 8 Photo showing the 3 mm wide band of 80 grit transition strip

UNCLASSIFIED 11

DSTOndashTRndash2898 UNCLASSIFIED

pressure range of the scanners is 249 kPa (ldquo10 inches-of-water scannerrdquo) and 689 kPa(ldquo1 psi scannerrdquo) The 689 kPa scanner was used to read the static pressure at the longi-tudinal ports as well as the output from the Preston tube and the Pitot-static probe

For the purpose of cross-checking and for redundancy the Preston tube was connectedto two independent ports of the 689 kPa scanner and the two readings averaged For thisscanner pressures could be read to an accuracy of 6890 times 00003 Pa ie about 2 Pa Theminimum ∆p measured by the Preston tube was 145 Pa which gives a pressure scannerresolution of 14 However this minimum ∆p was recorded for a location where thePreston tube was in a laminar boundary layer and such data is only useful in a qualitativesense (see Section 2) For locations were the boundary layer is turbulent the minimum ∆pwas 340 Pa which gives a pressure scanner resolution of 06 The 249 kPa scanner wasused mainly to acquire the static pressures at the lateral ports

35 Data Acquisition Software

A software package called ImPressOne was used which communicates with the PSI 8400and displays and acquires the pressure data for the model under test For the staticpressure measurements 100 readings were acquired at each pressure port at a samplingrate of 20 Hz For the Preston-tube measurements the sample rate was increased and100 samples were acquired at each pressure port at a sampling rate of 50 Hz for eachfree-stream velocity

36 Experimental Procedure

The hull was tested with each of the selected tripping devices listed in Table 1 as wellas without a tripping device resulting in five different test configurations For each testconfiguration the static pressures were initially acquired for that particular configurationfollowed by the Preston-tube measurements

A Preston tube having a diameter of 06 mm was attached to the surface of the modelusing both plasticine and tape to ensure that the tube was positioned as flat as possibleon the surface of the model as shown in Figure 9 Preston-tube measurement were takenon the upper surface of the submarine model along a line directly above the centre-lineof the model For the dT = 02 and 05 mm wires and the grit case measurements weretaken from x = 73 mm to x = 1065 mm for a total of 18 stations For the dT = 01 mmwire measurements were limited to 3 stations between x = 305 mm and x = 442 mmThe stream-wise coordinates for the Preston tube measurements are given in the Table 2Data were acquired for a range of free-stream velocities from 40 to 70 ms in incrementsof 5 ms

For each nominal velocity the corresponding model Reynolds number was calcu-lated assuming standard temperature and atmospheric pressure conditions 20C and101 325 Pa respectively For each given test the temperature and static pressure of theair within the test section were logged and the air density and viscosity were calculatedTo account for daily variations in temperature and atmospheric pressure the freestream

12 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Flow direction

Figure 9 Preston tube located on the centre-line of the upper-surface of submarine

velocity was adjusted to ensure that the model Reynolds number remained constant foreach given nominal velocity condition as shown in Table 3

Table 2 Skin-friction measurement stations Where applicable the corresponding staticport number is given For the dT = 01 mm wire measurements were only taken at stations3050 3600 as well as an additional station at x = 4425 mm

xmm 731 787 843 900 1125 1350 1575 1800 2150Static port - - - 6 - 7 - 8 -

xmm 2500 3050 3600 5250 7000 8700 9500 10100 10650Static port 9 - 12 13 14 17 18 21 24

Table 3 Reynolds numbers (based on submarine length 135 m) corresponding to thenominal free-stream velocities

Nominal Uinfin 40 45 50 55 60 65 70 msRe 358 403 448 493 537 582 627 times106

37 Data Reduction

The static pressure readings from the pressure ports were converted to pressure coefficientsusing the relationship

Cp =ps minus pinfinpt minus pinfin

(11)

where pinfin is the reference free-stream static pressure pt is the reference free-stream totalpressure and ps is the static pressure on the surface of the submarine model

As explained in Section 34 all Preston tube pressures are measured relative to the free-stream static pressure In order to apply the Preston tube calibration (4)-(6) the loggedPreston-tube pressure differences (ie pp minus pinfin) must first be converted to a ∆p = pp minus ps

UNCLASSIFIED 13

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 7: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

Simon HenbestAerospace Division

Simon Henbest obtained a Bachelor of Engineering (Mechan-ical) degree with honours in 1977 and a PhD in 1983 bothfrom The University of Melbourne His PhD titled rdquoThe Struc-ture of Turbulent Pipe Flowrdquo provide experimental support toTownsendrsquos attached eddy hypothesis for wall bounded flowsIn 1984 he was awarded an Australian National Research Fel-lowship and continued wall turbulence research at the Univer-sity of Melbourne In 1987 he commenced employment at theAeronautical Research Laboratories (now called the DefenceScience and Technology Organisation) and obtained merit pro-motions to both Senior Research Scientist and Principal Re-search Scientist While at DSTO he has been involved in re-search into high speed jet and aeroacoustic cavity flows the IRsignature prediction of aircraft numerous aerodynamic testingprogrammes He has acted as a Research Leader for extendedperiods in AVD AOD and HPPD He is currently Head of FluidMechanics in Aerospace Division

UNCLASSIFIED vii

DSTOndashTRndash2898 UNCLASSIFIED

THIS PAGE IS INTENTIONALLY BLANK

viii UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Contents

Glossary xi

Notation xi

1 Introduction 1

11 Boundary-Layer Transition 1

12 Approach of Erm amp Joubert (1991) 2

13 Empirical Expressions to Determine Sizes of Tripping Devices 4

2 Preston-Tube Method of Measuring Skin-Friction Coefficients 4

3 Test Program 7

31 Test Facility 7

32 Test Model 7

33 Tripping Devices 10

34 Pressure Scanners 10

35 Data Acquisition Software 12

36 Experimental Procedure 12

37 Data Reduction 13

4 Results 14

41 Skin Friction Without a Tripping Device 14

42 Skin Friction With Tripping Devices 16

421 Comparison of the Different Trip Devices 21

422 Scaling of Skin Friction with Reynolds Number 22

423 Over-stimulation and the Maximum Trip Reynolds Number 23

43 Pressure Coefficients 24

44 Pressure Gradients 26

5 Comparison with CFD Predictions 29

6 Conclusions 30

7 Acknowledgements 32

Appendices

UNCLASSIFIED ix

DSTOndashTRndash2898 UNCLASSIFIED

A Summary of Tripping Devices Used in Previous Experiments 35

B Preston Tube Data Processing 36

C Skin Friction Coefficients 37

D Pressure Coefficients 45

x UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Glossary

DARPA Defense Advanced Research Projects AgencyCERP Corporate Enabling Research ProgramCFD Computational Fluid DynamicsLSWT Low-Speed Wind TunnelDSTO Defence Science and Technology Organisation

Notation

Cf Local skin-friction coefficientCp Pressure coefficientd Outer diameter of Preston tubedT Diameter of trip wireh Height of grit transition strippinfin Free-stream static pressurepp Total pressure of Preston tubeps Model surface static pressurept Free-stream total pressurep+x Non-dimensional pressure gradient parameterRe Reynolds numberRedT Reynolds number based on diameter of wireRex Reynolds number based on the stream-wise coordinateRext Streamwise Reynolds number of transition pointU Streamwise velocity in boundary layerU1 Streamwise velocity at edge of boundary layerUinfin Nominal streamwise velocity in tunnel working-sectionUτ Friction velocityw Width of grit transition stripx Streamwise coordinatext Streamwise coordinate of transition pointy Wall normal coordinate∆p ∆p = pp minus psν Kinematic viscosityρ Fluid densityτ0 Wall shear stress

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DSTOndashTRndash2898 UNCLASSIFIED

THIS PAGE IS INTENTIONALLY BLANK

xii UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

1 Introduction

This work aims to understand flow fields about a submarine As part of this programa series of experiments have been conducted in the Low-Speed Wind Tunnel (LSWT) atthe Defence Science and Technology Organisation (DSTO) to quantify the skin-frictiondistributions on a generic submarine model and in the process investigate the effectivenessof a limited range of tripping devices The results also provide a reference data set forcomputational fluid dynamics (CFD) validation of a submarine model

When conducting tests in wind tunnels on a sub-scale model for results of the exper-iment to be transferable to the full-scale vehicle the flow patterns and load coefficientson the model and the full-size vehicle need to be made similar Ideally this is achievedthrough matching the Reynolds number of the flow over the model to that of the full-scalevehicle However in practice this is difficult to achieve and is not always possible To en-sure that the flow features on the model are representative of those for the full-size vehiclea tripping device can be used such that the boundary layers (ie regions of laminar flowlaminar-to-turbulent transition and turbulent flow) are made similar However differenttripping devices can impart different disturbances into the flow In order to correctly stim-ulate the boundary layer on the submarine model and avoid over- or under-stimulationthe type and size of tripping devices need to be selected for a given Reynolds numberor Reynolds number range and also for a specific trip location Additionally the chosentripping device will be specific to a given tunnel and would be dependent on factors suchas the level of free-stream turbulence in the tunnel

dT

Ud

Trip wire

xd

Laminar Transition Turbulent

Boundary-layeredge

U1

Figure 1 Diagrammatic representation of a boundary layer being tripped based on adiagram given by White (1974)

11 Boundary-Layer Transition

Boundary-layer transition is a complicated physical process dependent on instability mech-anisms including Tollmien-Schlichting waves crossflow and Gortler instabilities (see Reedamp Saric 2008) Over the years there have been numerous articles published on transi-tion both from experimental investigations and CFD analyses in low-speed transonic

UNCLASSIFIED 1

DSTOndashTRndash2898 UNCLASSIFIED

and hypersonic flow regimes (for example Schlatter amp Henningson 2009) Details of thetransition process are still not fully understood In the present report transition physicalprocesses are not considered instead attention is focused on how to stabilise the posi-tion of the transition using a tripping device and to ensure that the turbulent boundarylayer is neither under- or over-stimulated irrespective of the flow physics associated withtransition

12 Approach of Erm amp Joubert (1991)

A diagrammatic representation of a boundary layer being tripped is shown in Figure 1where dT is the height of the tripping device U1 is the streamwise velocity at the edge ofthe boundary layer xd is the location of the tripping device measured from the nose ofthe model and Ud is the velocity in the boundary layer at the top of the device

A question that had to be addressed was what is the best size and type of trippingdevice to use in the current experiments in the LSWT to trip the boundary layer on thesubmarine model Erm amp Joubert (1991) faced a similar question in their studies on low-Reynolds-number flows over a smooth flat surface in a zero pressure gradient For differenttypes of tripping devices they measured longitudinal skin-friction coefficients for a rangeof free-stream velocities Their data for a 12 mm wire tripping device are reproduced inFigure 2 From this figure it can be seen that as the velocity is increased from 8 ms thedevice imparts an increased amount of turbulent energy into the flow so that the laminar-to-turbulent transition region moves upstream They conjectured that correct stimulationis associated with a particular curve when the peaks of successive curves correspondingto higher velocities do not advance significantly upstream Velocities lower than thatcorresponding to the particular curve were obviously associated with under-stimulatedflows since the peaks of the curves were well downstream of the device and thus thedevice was therefore not completely effective in tripping the flow Since the velocitycorresponding to the particular curve establishes a turbulent boundary layer almost to thepossible upstream limit of turbulent flow it seemed reasonable to assume that the maineffect of higher velocities was to overstimulate the flow

The x-coordinate corresponding to the peaks of Figure 2 are plotted in Figure 3 as afunction of streamwise velocity and it is apparent that the above condition for correct stim-ulation was satisfied when the velocity was between 10 and 12 ms This corresponds to aminimum Reynolds number of the tripping device in the range of RedT = U1dT ν = 800to 960 where ν is the kinematic viscosity For the case where a trip device has aReynolds number greater than the minimum required the tripping device may overstim-ulate the flow Note over-stimulation does not necessarily result in higher skin-frictionwhen compared to a correctly stimulated layer Rather it means that the disturbanceintroduced by the tripping device is felt downstream of the transition region and leadsto a ldquonon-standardrdquo turbulent boundary initially developing Ideally to assess whetherover-stimulation has occurred complete velocity profiles in the turbulent region need tobe measured and compared against reference data sets such as those collated by Coles(1962)

It should be noted that in the current work the boundary layer develops in a pressuregradient with wall curvature in both the streamwise and spanwise directions Whereas

2 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

the work of Erm amp Joubert (1991) was undertaken on a flat plate zero pressure gradientthis means the RedT values given above cannot be applied directly to predict the trip sizerequired However the approach taken here broadly follows that of Erm amp Joubert (1991)in that a range of trip Reynolds numbers were tested (by varying both freestream velocityand trip size) and the skin-friction downstream of the trip measured

0 01 02x (m)

03 04 05

Figure 2 Cf vs x measurements for a 12 mm diameter trip wire for different free-streamvelocities as obtained by Erm amp Joubert (1991)

8 9 10 11 12 13 14

xlocation

(m)of

peakCf

Location of peak Cf

Location of trip device

01

02

0

Uinfin (ms)

Figure 3 Location of the peak Cf values shown in Figure 2

UNCLASSIFIED 3

DSTOndashTRndash2898 UNCLASSIFIED

13 Empirical Expressions to Determine Sizes of TrippingDevices

Researchers have proposed different empirical expressions for determining the size of deviceto use to trip the flow The relationships incorporate parameters including the height ofthe tripping device dT the velocity at the edge of the boundary layer U1 the velocity inthe undisturbed boundary layer at the top of the device Ud and the wall friction velocityevaluated at the device Uτ The friction velocity is defined by τ0 = ρU2

τ where τ0 is thesurface shear stress and ρ is the fluid density Recommendations for fully-effective trippingcover quite a wide range Tani et al (1940) proposed the criterion UτdT ν = 13 Fage ampPreston (1941) proposed UτdT ν = 20 Braslow amp Knox (1958) proposed UddT ν = 600and Gibbings (1959) proposed U1dT ν = 826 It should be noted that the criterion ofGibbings (1959) is based on a review of many data sets included those of Tani amp Sato(1956) and Fage amp Preston (1941) Gibbings (1959) expresses the Tani amp Sato (1956)and Fage amp Preston (1941) criteria as Reynolds numbers based on the freestream velocitywhich gives values of U1dT ν = 600 and 840 respectively The criterion given aboverepresent minimum values of the tripping device Reynolds number required to correctlytrip the boundary layer and agree with the results of Erm amp Joubert (1991)

An analysis of the literature for tests done on bodies of revolution indicated that thereis no consistent approach for selecting the size and type of device to use on such bodiesAppendix A gives details of devices used by different investigators for bodies of revolutiontogether with other experimental information Based on the freestream velocity and tripheight the Reynolds numbers of the trip devices given in Appendix A range from 200 to40 times 103 For the present investigation the approach used to establish the effects thatdifferent devices had on tripping laminar boundary layers was similar to that used byErm amp Joubert (1991) for a smooth flat plate in a zero pressure gradient Using theirtechnique it is possible to establish the size and type of tripping device to be used for agiven velocity to obtain correctly stimulated turbulent boundary layers

2 Preston-Tube Method of Measuring

Skin-Friction Coefficients

Skin-friction coefficients in a turbulent boundary layer flowing over a smooth surface canbe measured in a number of different ways (Fernholz et al 1996) including using Prestontubes (Preston 1954) from velocity profiles and using devices mounted flush with thesurface of a model Of the alternative approaches the Preston-tube method is convenientand is widely used The method makes use of a simple Pitot tube placed on the surfaceof a body and when used this way it is termed a Preston tube The method depends onan underlining assumption that in the region adjacent to the surface the flow is primarilydetermined by the surface shear stress and the properties of the fluid and is independentof factors such as pressure gradient and surface curvature The assumption implies thatthe velocity profile in a turbulent boundary layer adjacent to the surface is given by

U

Uτ= f

(Uτy

ν

)(1)

4 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

where U is the local stream-wise velocity Uτ is the friction velocity f is a universalfunction y is the wall normal coordinate and ν is the kinematic viscosity Equation (1) isoften referred to as the ldquolaw of the wallrdquo (Coles 1956)

A Pitot tube placed on the wall will measure a pressure relative to the wall staticpressure of ∆p = ρU22 at an effective coordinate y = c0d where d is the outer diameterof the Pitot tube and c0 is an unknown constant Substituting the values U =

radic(2∆pρ)

and y = cod into (1) yields a relationship between the wall shear stress fluid propertiesPreston-tube pressure difference and the tube diameter which is given by

2∆p

ρUτ2 =

[f

(Uτ c0d

ν

)]2 (2)

Alternatively for the purpose of measuring skin friction (2) can be expressed more con-veniently in the form

τ0d2

4ρν2= F

(∆pd2

4ρν2

)(3)

where c0 has been absorbed into the function F The function F represents the ldquocalibra-tionrdquo function for a Preston tube and several experimentally derived forms exist in theliterature (see Preston 1954 Patel 1965 Zagarola et al 2001) Generally the calibrationis determined by placing the Preston tube in a pipe flow where the wall shear stress (orfriction factor) can be determined accurately by measuring the pressure gradient in thepipe

For the data presented in this report the calibration of Patel (1965) was used todetermine the wall shear stress The calibration curve of Patel (1965) is given as follows

xlowast =ylowast + 2 log10(195ylowast + 410) for 55 ltUτd

2νlt 800 (4)

ylowast =08287 minus 01381xlowast + 01437xlowast2 minus 0006xlowast3 for 56 ltUτd

2νlt 55 and (5)

ylowast =1

2xlowast + 0037 for

Uτd

2νlt 56 (6)

where

xlowast = log10

(∆pd2

4ρν2

)and ylowast = log10

(τ0d

2

4ρν2

)

The local skin friction coefficient Cf is then found using

Cf =τ0

12ρU

21

(7)

where U1 is the streamwise velocity at the edge of the boundary layer

The calibration given by (4)-(6) is valid only for a hydrodynamically smooth surfaceA surface is considered hydrodynamically smooth provided that the height of surfaceroughness elements remain less than 5νUτ (Jimenez 2004) The minimum value of 5νUτthat was measured was approximately 4microm and the measured surface finish was found tobe an order of magnitude less than this value (Section 32) Hence the requirement of ahydrodynamically smooth surface is satisfied for this experiment

UNCLASSIFIED 5

DSTOndashTRndash2898 UNCLASSIFIED

The fundamental requirement for using a Preston tube is that the boundary layer isin a turbulent state and that the dimension of the Preston tube is such that it remainswithin the region where (1) is valid (ie from (4) Uτdν lt 1600) The diameter of thePreston tube for all experiments was d = 06 mm and this ensured that Uτdν remainedless than 1600 well within the range of the calibration (4)

It is known that for sufficiently strong pressure gradients the form of (1) changes (seeNickels 2004) Patel (1965) quantifies the effect of pressure gradients using the non-dimensional pressure gradient parameter1

p+x =ν

ρU3τ

dp

dx (8)

The error associated with using a Preston tube in pressure gradients is quantified by Patel(1965) and is given by the following inequalities

1 Adverse pressure gradient

Max Error 3 0 lt p+x lt 001 andUτd

νle 200 (9a)

Max Error 6 0 lt p+x lt 0015 andUτd

νle 250 (9b)

2 Favourable pressure gradient

Max Error 3 minus0005 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10a)

Max Error 6 minus0007 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10b)

The pressure gradient data are presented in Section 44 and were found to fall within thelimits of (9a) and (10a) indicating that the skin-friction coefficients are valid to withinplusmn3 This accuracy is similar to the alternative direct skin-friction measuring techniqueswhich typically achieve an accuracy of plusmn4 (Fernholz et al 1996)

The effect of model spanwise curvature on (4)-(6) is not quantified A reasonableassumption is that since the boundary layer thickness is much less than the model diameterthe effect of spanwise model curvature can be neglected

The Preston-tube method as outlined above requires that the boundary layer is in aturbulent state For this reason the method cannot be used to infer the skin friction atlocations were the boundary layer is in a laminar state However the ∆p values read by thePreston tube can be used to determine where laminar-to-turbulent transition occurs Theregion of transition is associated with a discontinuity in ∆p when plotted as a functionof streamwise coordinate x as shown by Erm amp Joubert (1991)

1for clarity we have adopted the notation for the pressure gradient parameter used by Nickels (2004)Patel (1965) uses the symbol ∆

6 UNCLASSIFIED

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Figure 4 LSWT Layout see Erm (2003)

3 Test Program

In this preliminary investigation four different tripping devices were used to investigatethe effect of the device on the skin-friction profile of a generic sub-scale submarine modelTests were conducted both with and without the tripping devices at a range of nominalfree-stream velocities Uinfin ranging from Uinfin = 40 to 70 ms to assess their effectivenessin tripping the boundary layer

31 Test Facility

The Low-Speed Wind Tunnel at DSTO is a closed circuit continuous flow tunnel with acontraction ratio of 41 The test section has an irregular octagonal shape with a heightof 213 m a width of 274 m and a length of 6553 m with a longitudinal turbulenceintensity of approximately 04 in the region where the models are tested (see Erm2003) An outline of the plan of the wind tunnel is shown in Figure 4 Free-streamvelocities were measured using static pressure rings at the upstream and downstreamends of the contraction A Pitot-static probe mounted on the side wall near the front ofthe working section was used to provide an independent measurement of the free-streamvelocity

32 Test Model

The sub-scale submarine model utilised in these tests is referred to as the Joubert modelsince the geometry is based on the work of Joubert (2004) and Joubert (2006) as well asLoid amp Bystrom (1983) The model was designed for the purpose of experimental and

UNCLASSIFIED 7

DSTOndashTRndash2898 UNCLASSIFIED

1

2 345

6 7 8 91011

12 13 141516

17 181920

212223

24 252627

28 29 303132

33 34

35

Top view

Side view

Figure 5 Schematic of scale model showing static-pressure port locations green and redmarkers represent the starboard and port static-pressure ports respectively

numerical studies and has no full-scale equivalent While the full model includes a casingcentre fin and control surfaces all tests reported here were conducted on the axisymmetricbody shape only

The model was machined from aluminum and consists of an ellipsoidal nose a cylin-drical centre-body and a streamlined tail section At the design stage an N6 surface finishwas specified for the model which corresponds to a roughness of 08microm in waviness Af-ter manufacture the surface finish was checked using a Surface Roughness Indicator andthe finish was found to be better than the design specification The model was anodisedwhich increased the thickness of the natural oxide layer by about 10microm

The model is 1350 mm long with a maximum diameter of 185 mm and slendernessratio of 73 where the slenderness ratio is defined as hull length divided by maximumhull diameter The model contains 21 longitudinal static-pressure ports on the centre-lineof the upper surface and 14 lateral static-pressure ports offset to the port and starboardsides of the upper surface centre-line Figure 5 shows the stream-wise location of thestatic-pressure ports

The model was supported by a single pylon as shown in Figure 6 All tests were carriedout at zero angle of yaw and zero angle of pitch The origin of the body coordinate systemis located at the nose of the submarine model The x-axis corresponds to the axis ofsymmetry of the model

8 UNCLASSIFIED

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Figure 6 Submarine model mounted in LSWT showing pylon support and pitch controlarm

UNCLASSIFIED 9

DSTOndashTRndash2898 UNCLASSIFIED

Table 1 Details of tripping devices where the Reynolds number is based on the height ofthe device The minimum Reynolds number and maximum Reynolds number correspondto nominal freestream velocities of Uinfin = 40 ms and Uinfin = 70 ms respectively where his the height of the grit and w is the width of the grit

Device Dimensions (mm) RedT (min) RedT (max)

Wire 1 dT = 01 281 496Wire 2 dT = 02 577 1015Wire 3 dT = 05 1443 256680 Grit h = 021 w = 3 605 1073

33 Tripping Devices

In this work four tripping devices were tested and consisted of circular wires with diame-ters dT = 01 02 and 05 mm as well as a distributed silicon carbide grit of size 80 havinga width of 3 mm The circular wires were bent to conform to the local diameter of thesubmarine and then attached with ldquosuper-gluerdquo such that there was no gap between thewire and the model surface Figure 7 The silicon carbide grit is prepared by distributinga layer of grit on double-sided sticky tape the tape is then adhered to the submarineFigure 8 The tripping devices were attached to the submarine model circumferentiallylocated at a streamwise coordinate of x = 675 mm measured from the nose of the sub-marine which corresponds to 5 of the total model length The dimensions of the tripdevices along with the Reynolds number range of the trip devices are summarised inTable 1 Note that the Reynolds number of the trip device is defined as RedT = U1dT νwhere for the case of the 80 grit dT is replaced by the grit height h

34 Pressure Scanners

Pressure Systems Incorporated (PSI) brand pressure scanners were used to measure allstatic and total pressures The pressure scanners are differential pressure measurementunits consisting of an array of silicon piezoresistive pressure sensors one for each pressureport The outputs of the sensors are electronically multiplexed through a single on-boardinstrumentation amplifier using binary addressing The scanners include a two-positioncalibration manifold actuated by momentary pulses of control pressures In the calibrateposition all sensors are connected to a common calibration pressure port A series ofaccurately-measured pressures is applied through this port to characterize the sensorsProper and periodic on-line calibration maintains static errors within plusmn003 or betterof the full-scale pressure range

The pressure scanners are controlled and sampled using a PSI 8400 electronic measure-ment system It is a modular parallel processing system for high-speed pressure scanningat up to 20000 measurements per second and allows the use of digitally temperaturecompensated pressure scanners

Two differential pressure scanners were used in the experiments All pressures aremeasured relative to the free-stream static pressure pinfin as measured by the referencefree-stream Pitot-static probe Each pressure scanner contained 32 ports The full-scale

10 UNCLASSIFIED

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Figure 7 Location of trip wire

Figure 8 Photo showing the 3 mm wide band of 80 grit transition strip

UNCLASSIFIED 11

DSTOndashTRndash2898 UNCLASSIFIED

pressure range of the scanners is 249 kPa (ldquo10 inches-of-water scannerrdquo) and 689 kPa(ldquo1 psi scannerrdquo) The 689 kPa scanner was used to read the static pressure at the longi-tudinal ports as well as the output from the Preston tube and the Pitot-static probe

For the purpose of cross-checking and for redundancy the Preston tube was connectedto two independent ports of the 689 kPa scanner and the two readings averaged For thisscanner pressures could be read to an accuracy of 6890 times 00003 Pa ie about 2 Pa Theminimum ∆p measured by the Preston tube was 145 Pa which gives a pressure scannerresolution of 14 However this minimum ∆p was recorded for a location where thePreston tube was in a laminar boundary layer and such data is only useful in a qualitativesense (see Section 2) For locations were the boundary layer is turbulent the minimum ∆pwas 340 Pa which gives a pressure scanner resolution of 06 The 249 kPa scanner wasused mainly to acquire the static pressures at the lateral ports

35 Data Acquisition Software

A software package called ImPressOne was used which communicates with the PSI 8400and displays and acquires the pressure data for the model under test For the staticpressure measurements 100 readings were acquired at each pressure port at a samplingrate of 20 Hz For the Preston-tube measurements the sample rate was increased and100 samples were acquired at each pressure port at a sampling rate of 50 Hz for eachfree-stream velocity

36 Experimental Procedure

The hull was tested with each of the selected tripping devices listed in Table 1 as wellas without a tripping device resulting in five different test configurations For each testconfiguration the static pressures were initially acquired for that particular configurationfollowed by the Preston-tube measurements

A Preston tube having a diameter of 06 mm was attached to the surface of the modelusing both plasticine and tape to ensure that the tube was positioned as flat as possibleon the surface of the model as shown in Figure 9 Preston-tube measurement were takenon the upper surface of the submarine model along a line directly above the centre-lineof the model For the dT = 02 and 05 mm wires and the grit case measurements weretaken from x = 73 mm to x = 1065 mm for a total of 18 stations For the dT = 01 mmwire measurements were limited to 3 stations between x = 305 mm and x = 442 mmThe stream-wise coordinates for the Preston tube measurements are given in the Table 2Data were acquired for a range of free-stream velocities from 40 to 70 ms in incrementsof 5 ms

For each nominal velocity the corresponding model Reynolds number was calcu-lated assuming standard temperature and atmospheric pressure conditions 20C and101 325 Pa respectively For each given test the temperature and static pressure of theair within the test section were logged and the air density and viscosity were calculatedTo account for daily variations in temperature and atmospheric pressure the freestream

12 UNCLASSIFIED

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Flow direction

Figure 9 Preston tube located on the centre-line of the upper-surface of submarine

velocity was adjusted to ensure that the model Reynolds number remained constant foreach given nominal velocity condition as shown in Table 3

Table 2 Skin-friction measurement stations Where applicable the corresponding staticport number is given For the dT = 01 mm wire measurements were only taken at stations3050 3600 as well as an additional station at x = 4425 mm

xmm 731 787 843 900 1125 1350 1575 1800 2150Static port - - - 6 - 7 - 8 -

xmm 2500 3050 3600 5250 7000 8700 9500 10100 10650Static port 9 - 12 13 14 17 18 21 24

Table 3 Reynolds numbers (based on submarine length 135 m) corresponding to thenominal free-stream velocities

Nominal Uinfin 40 45 50 55 60 65 70 msRe 358 403 448 493 537 582 627 times106

37 Data Reduction

The static pressure readings from the pressure ports were converted to pressure coefficientsusing the relationship

Cp =ps minus pinfinpt minus pinfin

(11)

where pinfin is the reference free-stream static pressure pt is the reference free-stream totalpressure and ps is the static pressure on the surface of the submarine model

As explained in Section 34 all Preston tube pressures are measured relative to the free-stream static pressure In order to apply the Preston tube calibration (4)-(6) the loggedPreston-tube pressure differences (ie pp minus pinfin) must first be converted to a ∆p = pp minus ps

UNCLASSIFIED 13

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 8: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

THIS PAGE IS INTENTIONALLY BLANK

viii UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Contents

Glossary xi

Notation xi

1 Introduction 1

11 Boundary-Layer Transition 1

12 Approach of Erm amp Joubert (1991) 2

13 Empirical Expressions to Determine Sizes of Tripping Devices 4

2 Preston-Tube Method of Measuring Skin-Friction Coefficients 4

3 Test Program 7

31 Test Facility 7

32 Test Model 7

33 Tripping Devices 10

34 Pressure Scanners 10

35 Data Acquisition Software 12

36 Experimental Procedure 12

37 Data Reduction 13

4 Results 14

41 Skin Friction Without a Tripping Device 14

42 Skin Friction With Tripping Devices 16

421 Comparison of the Different Trip Devices 21

422 Scaling of Skin Friction with Reynolds Number 22

423 Over-stimulation and the Maximum Trip Reynolds Number 23

43 Pressure Coefficients 24

44 Pressure Gradients 26

5 Comparison with CFD Predictions 29

6 Conclusions 30

7 Acknowledgements 32

Appendices

UNCLASSIFIED ix

DSTOndashTRndash2898 UNCLASSIFIED

A Summary of Tripping Devices Used in Previous Experiments 35

B Preston Tube Data Processing 36

C Skin Friction Coefficients 37

D Pressure Coefficients 45

x UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Glossary

DARPA Defense Advanced Research Projects AgencyCERP Corporate Enabling Research ProgramCFD Computational Fluid DynamicsLSWT Low-Speed Wind TunnelDSTO Defence Science and Technology Organisation

Notation

Cf Local skin-friction coefficientCp Pressure coefficientd Outer diameter of Preston tubedT Diameter of trip wireh Height of grit transition strippinfin Free-stream static pressurepp Total pressure of Preston tubeps Model surface static pressurept Free-stream total pressurep+x Non-dimensional pressure gradient parameterRe Reynolds numberRedT Reynolds number based on diameter of wireRex Reynolds number based on the stream-wise coordinateRext Streamwise Reynolds number of transition pointU Streamwise velocity in boundary layerU1 Streamwise velocity at edge of boundary layerUinfin Nominal streamwise velocity in tunnel working-sectionUτ Friction velocityw Width of grit transition stripx Streamwise coordinatext Streamwise coordinate of transition pointy Wall normal coordinate∆p ∆p = pp minus psν Kinematic viscosityρ Fluid densityτ0 Wall shear stress

UNCLASSIFIED xi

DSTOndashTRndash2898 UNCLASSIFIED

THIS PAGE IS INTENTIONALLY BLANK

xii UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

1 Introduction

This work aims to understand flow fields about a submarine As part of this programa series of experiments have been conducted in the Low-Speed Wind Tunnel (LSWT) atthe Defence Science and Technology Organisation (DSTO) to quantify the skin-frictiondistributions on a generic submarine model and in the process investigate the effectivenessof a limited range of tripping devices The results also provide a reference data set forcomputational fluid dynamics (CFD) validation of a submarine model

When conducting tests in wind tunnels on a sub-scale model for results of the exper-iment to be transferable to the full-scale vehicle the flow patterns and load coefficientson the model and the full-size vehicle need to be made similar Ideally this is achievedthrough matching the Reynolds number of the flow over the model to that of the full-scalevehicle However in practice this is difficult to achieve and is not always possible To en-sure that the flow features on the model are representative of those for the full-size vehiclea tripping device can be used such that the boundary layers (ie regions of laminar flowlaminar-to-turbulent transition and turbulent flow) are made similar However differenttripping devices can impart different disturbances into the flow In order to correctly stim-ulate the boundary layer on the submarine model and avoid over- or under-stimulationthe type and size of tripping devices need to be selected for a given Reynolds numberor Reynolds number range and also for a specific trip location Additionally the chosentripping device will be specific to a given tunnel and would be dependent on factors suchas the level of free-stream turbulence in the tunnel

dT

Ud

Trip wire

xd

Laminar Transition Turbulent

Boundary-layeredge

U1

Figure 1 Diagrammatic representation of a boundary layer being tripped based on adiagram given by White (1974)

11 Boundary-Layer Transition

Boundary-layer transition is a complicated physical process dependent on instability mech-anisms including Tollmien-Schlichting waves crossflow and Gortler instabilities (see Reedamp Saric 2008) Over the years there have been numerous articles published on transi-tion both from experimental investigations and CFD analyses in low-speed transonic

UNCLASSIFIED 1

DSTOndashTRndash2898 UNCLASSIFIED

and hypersonic flow regimes (for example Schlatter amp Henningson 2009) Details of thetransition process are still not fully understood In the present report transition physicalprocesses are not considered instead attention is focused on how to stabilise the posi-tion of the transition using a tripping device and to ensure that the turbulent boundarylayer is neither under- or over-stimulated irrespective of the flow physics associated withtransition

12 Approach of Erm amp Joubert (1991)

A diagrammatic representation of a boundary layer being tripped is shown in Figure 1where dT is the height of the tripping device U1 is the streamwise velocity at the edge ofthe boundary layer xd is the location of the tripping device measured from the nose ofthe model and Ud is the velocity in the boundary layer at the top of the device

A question that had to be addressed was what is the best size and type of trippingdevice to use in the current experiments in the LSWT to trip the boundary layer on thesubmarine model Erm amp Joubert (1991) faced a similar question in their studies on low-Reynolds-number flows over a smooth flat surface in a zero pressure gradient For differenttypes of tripping devices they measured longitudinal skin-friction coefficients for a rangeof free-stream velocities Their data for a 12 mm wire tripping device are reproduced inFigure 2 From this figure it can be seen that as the velocity is increased from 8 ms thedevice imparts an increased amount of turbulent energy into the flow so that the laminar-to-turbulent transition region moves upstream They conjectured that correct stimulationis associated with a particular curve when the peaks of successive curves correspondingto higher velocities do not advance significantly upstream Velocities lower than thatcorresponding to the particular curve were obviously associated with under-stimulatedflows since the peaks of the curves were well downstream of the device and thus thedevice was therefore not completely effective in tripping the flow Since the velocitycorresponding to the particular curve establishes a turbulent boundary layer almost to thepossible upstream limit of turbulent flow it seemed reasonable to assume that the maineffect of higher velocities was to overstimulate the flow

The x-coordinate corresponding to the peaks of Figure 2 are plotted in Figure 3 as afunction of streamwise velocity and it is apparent that the above condition for correct stim-ulation was satisfied when the velocity was between 10 and 12 ms This corresponds to aminimum Reynolds number of the tripping device in the range of RedT = U1dT ν = 800to 960 where ν is the kinematic viscosity For the case where a trip device has aReynolds number greater than the minimum required the tripping device may overstim-ulate the flow Note over-stimulation does not necessarily result in higher skin-frictionwhen compared to a correctly stimulated layer Rather it means that the disturbanceintroduced by the tripping device is felt downstream of the transition region and leadsto a ldquonon-standardrdquo turbulent boundary initially developing Ideally to assess whetherover-stimulation has occurred complete velocity profiles in the turbulent region need tobe measured and compared against reference data sets such as those collated by Coles(1962)

It should be noted that in the current work the boundary layer develops in a pressuregradient with wall curvature in both the streamwise and spanwise directions Whereas

2 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

the work of Erm amp Joubert (1991) was undertaken on a flat plate zero pressure gradientthis means the RedT values given above cannot be applied directly to predict the trip sizerequired However the approach taken here broadly follows that of Erm amp Joubert (1991)in that a range of trip Reynolds numbers were tested (by varying both freestream velocityand trip size) and the skin-friction downstream of the trip measured

0 01 02x (m)

03 04 05

Figure 2 Cf vs x measurements for a 12 mm diameter trip wire for different free-streamvelocities as obtained by Erm amp Joubert (1991)

8 9 10 11 12 13 14

xlocation

(m)of

peakCf

Location of peak Cf

Location of trip device

01

02

0

Uinfin (ms)

Figure 3 Location of the peak Cf values shown in Figure 2

UNCLASSIFIED 3

DSTOndashTRndash2898 UNCLASSIFIED

13 Empirical Expressions to Determine Sizes of TrippingDevices

Researchers have proposed different empirical expressions for determining the size of deviceto use to trip the flow The relationships incorporate parameters including the height ofthe tripping device dT the velocity at the edge of the boundary layer U1 the velocity inthe undisturbed boundary layer at the top of the device Ud and the wall friction velocityevaluated at the device Uτ The friction velocity is defined by τ0 = ρU2

τ where τ0 is thesurface shear stress and ρ is the fluid density Recommendations for fully-effective trippingcover quite a wide range Tani et al (1940) proposed the criterion UτdT ν = 13 Fage ampPreston (1941) proposed UτdT ν = 20 Braslow amp Knox (1958) proposed UddT ν = 600and Gibbings (1959) proposed U1dT ν = 826 It should be noted that the criterion ofGibbings (1959) is based on a review of many data sets included those of Tani amp Sato(1956) and Fage amp Preston (1941) Gibbings (1959) expresses the Tani amp Sato (1956)and Fage amp Preston (1941) criteria as Reynolds numbers based on the freestream velocitywhich gives values of U1dT ν = 600 and 840 respectively The criterion given aboverepresent minimum values of the tripping device Reynolds number required to correctlytrip the boundary layer and agree with the results of Erm amp Joubert (1991)

An analysis of the literature for tests done on bodies of revolution indicated that thereis no consistent approach for selecting the size and type of device to use on such bodiesAppendix A gives details of devices used by different investigators for bodies of revolutiontogether with other experimental information Based on the freestream velocity and tripheight the Reynolds numbers of the trip devices given in Appendix A range from 200 to40 times 103 For the present investigation the approach used to establish the effects thatdifferent devices had on tripping laminar boundary layers was similar to that used byErm amp Joubert (1991) for a smooth flat plate in a zero pressure gradient Using theirtechnique it is possible to establish the size and type of tripping device to be used for agiven velocity to obtain correctly stimulated turbulent boundary layers

2 Preston-Tube Method of Measuring

Skin-Friction Coefficients

Skin-friction coefficients in a turbulent boundary layer flowing over a smooth surface canbe measured in a number of different ways (Fernholz et al 1996) including using Prestontubes (Preston 1954) from velocity profiles and using devices mounted flush with thesurface of a model Of the alternative approaches the Preston-tube method is convenientand is widely used The method makes use of a simple Pitot tube placed on the surfaceof a body and when used this way it is termed a Preston tube The method depends onan underlining assumption that in the region adjacent to the surface the flow is primarilydetermined by the surface shear stress and the properties of the fluid and is independentof factors such as pressure gradient and surface curvature The assumption implies thatthe velocity profile in a turbulent boundary layer adjacent to the surface is given by

U

Uτ= f

(Uτy

ν

)(1)

4 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

where U is the local stream-wise velocity Uτ is the friction velocity f is a universalfunction y is the wall normal coordinate and ν is the kinematic viscosity Equation (1) isoften referred to as the ldquolaw of the wallrdquo (Coles 1956)

A Pitot tube placed on the wall will measure a pressure relative to the wall staticpressure of ∆p = ρU22 at an effective coordinate y = c0d where d is the outer diameterof the Pitot tube and c0 is an unknown constant Substituting the values U =

radic(2∆pρ)

and y = cod into (1) yields a relationship between the wall shear stress fluid propertiesPreston-tube pressure difference and the tube diameter which is given by

2∆p

ρUτ2 =

[f

(Uτ c0d

ν

)]2 (2)

Alternatively for the purpose of measuring skin friction (2) can be expressed more con-veniently in the form

τ0d2

4ρν2= F

(∆pd2

4ρν2

)(3)

where c0 has been absorbed into the function F The function F represents the ldquocalibra-tionrdquo function for a Preston tube and several experimentally derived forms exist in theliterature (see Preston 1954 Patel 1965 Zagarola et al 2001) Generally the calibrationis determined by placing the Preston tube in a pipe flow where the wall shear stress (orfriction factor) can be determined accurately by measuring the pressure gradient in thepipe

For the data presented in this report the calibration of Patel (1965) was used todetermine the wall shear stress The calibration curve of Patel (1965) is given as follows

xlowast =ylowast + 2 log10(195ylowast + 410) for 55 ltUτd

2νlt 800 (4)

ylowast =08287 minus 01381xlowast + 01437xlowast2 minus 0006xlowast3 for 56 ltUτd

2νlt 55 and (5)

ylowast =1

2xlowast + 0037 for

Uτd

2νlt 56 (6)

where

xlowast = log10

(∆pd2

4ρν2

)and ylowast = log10

(τ0d

2

4ρν2

)

The local skin friction coefficient Cf is then found using

Cf =τ0

12ρU

21

(7)

where U1 is the streamwise velocity at the edge of the boundary layer

The calibration given by (4)-(6) is valid only for a hydrodynamically smooth surfaceA surface is considered hydrodynamically smooth provided that the height of surfaceroughness elements remain less than 5νUτ (Jimenez 2004) The minimum value of 5νUτthat was measured was approximately 4microm and the measured surface finish was found tobe an order of magnitude less than this value (Section 32) Hence the requirement of ahydrodynamically smooth surface is satisfied for this experiment

UNCLASSIFIED 5

DSTOndashTRndash2898 UNCLASSIFIED

The fundamental requirement for using a Preston tube is that the boundary layer isin a turbulent state and that the dimension of the Preston tube is such that it remainswithin the region where (1) is valid (ie from (4) Uτdν lt 1600) The diameter of thePreston tube for all experiments was d = 06 mm and this ensured that Uτdν remainedless than 1600 well within the range of the calibration (4)

It is known that for sufficiently strong pressure gradients the form of (1) changes (seeNickels 2004) Patel (1965) quantifies the effect of pressure gradients using the non-dimensional pressure gradient parameter1

p+x =ν

ρU3τ

dp

dx (8)

The error associated with using a Preston tube in pressure gradients is quantified by Patel(1965) and is given by the following inequalities

1 Adverse pressure gradient

Max Error 3 0 lt p+x lt 001 andUτd

νle 200 (9a)

Max Error 6 0 lt p+x lt 0015 andUτd

νle 250 (9b)

2 Favourable pressure gradient

Max Error 3 minus0005 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10a)

Max Error 6 minus0007 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10b)

The pressure gradient data are presented in Section 44 and were found to fall within thelimits of (9a) and (10a) indicating that the skin-friction coefficients are valid to withinplusmn3 This accuracy is similar to the alternative direct skin-friction measuring techniqueswhich typically achieve an accuracy of plusmn4 (Fernholz et al 1996)

The effect of model spanwise curvature on (4)-(6) is not quantified A reasonableassumption is that since the boundary layer thickness is much less than the model diameterthe effect of spanwise model curvature can be neglected

The Preston-tube method as outlined above requires that the boundary layer is in aturbulent state For this reason the method cannot be used to infer the skin friction atlocations were the boundary layer is in a laminar state However the ∆p values read by thePreston tube can be used to determine where laminar-to-turbulent transition occurs Theregion of transition is associated with a discontinuity in ∆p when plotted as a functionof streamwise coordinate x as shown by Erm amp Joubert (1991)

1for clarity we have adopted the notation for the pressure gradient parameter used by Nickels (2004)Patel (1965) uses the symbol ∆

6 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 4 LSWT Layout see Erm (2003)

3 Test Program

In this preliminary investigation four different tripping devices were used to investigatethe effect of the device on the skin-friction profile of a generic sub-scale submarine modelTests were conducted both with and without the tripping devices at a range of nominalfree-stream velocities Uinfin ranging from Uinfin = 40 to 70 ms to assess their effectivenessin tripping the boundary layer

31 Test Facility

The Low-Speed Wind Tunnel at DSTO is a closed circuit continuous flow tunnel with acontraction ratio of 41 The test section has an irregular octagonal shape with a heightof 213 m a width of 274 m and a length of 6553 m with a longitudinal turbulenceintensity of approximately 04 in the region where the models are tested (see Erm2003) An outline of the plan of the wind tunnel is shown in Figure 4 Free-streamvelocities were measured using static pressure rings at the upstream and downstreamends of the contraction A Pitot-static probe mounted on the side wall near the front ofthe working section was used to provide an independent measurement of the free-streamvelocity

32 Test Model

The sub-scale submarine model utilised in these tests is referred to as the Joubert modelsince the geometry is based on the work of Joubert (2004) and Joubert (2006) as well asLoid amp Bystrom (1983) The model was designed for the purpose of experimental and

UNCLASSIFIED 7

DSTOndashTRndash2898 UNCLASSIFIED

1

2 345

6 7 8 91011

12 13 141516

17 181920

212223

24 252627

28 29 303132

33 34

35

Top view

Side view

Figure 5 Schematic of scale model showing static-pressure port locations green and redmarkers represent the starboard and port static-pressure ports respectively

numerical studies and has no full-scale equivalent While the full model includes a casingcentre fin and control surfaces all tests reported here were conducted on the axisymmetricbody shape only

The model was machined from aluminum and consists of an ellipsoidal nose a cylin-drical centre-body and a streamlined tail section At the design stage an N6 surface finishwas specified for the model which corresponds to a roughness of 08microm in waviness Af-ter manufacture the surface finish was checked using a Surface Roughness Indicator andthe finish was found to be better than the design specification The model was anodisedwhich increased the thickness of the natural oxide layer by about 10microm

The model is 1350 mm long with a maximum diameter of 185 mm and slendernessratio of 73 where the slenderness ratio is defined as hull length divided by maximumhull diameter The model contains 21 longitudinal static-pressure ports on the centre-lineof the upper surface and 14 lateral static-pressure ports offset to the port and starboardsides of the upper surface centre-line Figure 5 shows the stream-wise location of thestatic-pressure ports

The model was supported by a single pylon as shown in Figure 6 All tests were carriedout at zero angle of yaw and zero angle of pitch The origin of the body coordinate systemis located at the nose of the submarine model The x-axis corresponds to the axis ofsymmetry of the model

8 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 6 Submarine model mounted in LSWT showing pylon support and pitch controlarm

UNCLASSIFIED 9

DSTOndashTRndash2898 UNCLASSIFIED

Table 1 Details of tripping devices where the Reynolds number is based on the height ofthe device The minimum Reynolds number and maximum Reynolds number correspondto nominal freestream velocities of Uinfin = 40 ms and Uinfin = 70 ms respectively where his the height of the grit and w is the width of the grit

Device Dimensions (mm) RedT (min) RedT (max)

Wire 1 dT = 01 281 496Wire 2 dT = 02 577 1015Wire 3 dT = 05 1443 256680 Grit h = 021 w = 3 605 1073

33 Tripping Devices

In this work four tripping devices were tested and consisted of circular wires with diame-ters dT = 01 02 and 05 mm as well as a distributed silicon carbide grit of size 80 havinga width of 3 mm The circular wires were bent to conform to the local diameter of thesubmarine and then attached with ldquosuper-gluerdquo such that there was no gap between thewire and the model surface Figure 7 The silicon carbide grit is prepared by distributinga layer of grit on double-sided sticky tape the tape is then adhered to the submarineFigure 8 The tripping devices were attached to the submarine model circumferentiallylocated at a streamwise coordinate of x = 675 mm measured from the nose of the sub-marine which corresponds to 5 of the total model length The dimensions of the tripdevices along with the Reynolds number range of the trip devices are summarised inTable 1 Note that the Reynolds number of the trip device is defined as RedT = U1dT νwhere for the case of the 80 grit dT is replaced by the grit height h

34 Pressure Scanners

Pressure Systems Incorporated (PSI) brand pressure scanners were used to measure allstatic and total pressures The pressure scanners are differential pressure measurementunits consisting of an array of silicon piezoresistive pressure sensors one for each pressureport The outputs of the sensors are electronically multiplexed through a single on-boardinstrumentation amplifier using binary addressing The scanners include a two-positioncalibration manifold actuated by momentary pulses of control pressures In the calibrateposition all sensors are connected to a common calibration pressure port A series ofaccurately-measured pressures is applied through this port to characterize the sensorsProper and periodic on-line calibration maintains static errors within plusmn003 or betterof the full-scale pressure range

The pressure scanners are controlled and sampled using a PSI 8400 electronic measure-ment system It is a modular parallel processing system for high-speed pressure scanningat up to 20000 measurements per second and allows the use of digitally temperaturecompensated pressure scanners

Two differential pressure scanners were used in the experiments All pressures aremeasured relative to the free-stream static pressure pinfin as measured by the referencefree-stream Pitot-static probe Each pressure scanner contained 32 ports The full-scale

10 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 7 Location of trip wire

Figure 8 Photo showing the 3 mm wide band of 80 grit transition strip

UNCLASSIFIED 11

DSTOndashTRndash2898 UNCLASSIFIED

pressure range of the scanners is 249 kPa (ldquo10 inches-of-water scannerrdquo) and 689 kPa(ldquo1 psi scannerrdquo) The 689 kPa scanner was used to read the static pressure at the longi-tudinal ports as well as the output from the Preston tube and the Pitot-static probe

For the purpose of cross-checking and for redundancy the Preston tube was connectedto two independent ports of the 689 kPa scanner and the two readings averaged For thisscanner pressures could be read to an accuracy of 6890 times 00003 Pa ie about 2 Pa Theminimum ∆p measured by the Preston tube was 145 Pa which gives a pressure scannerresolution of 14 However this minimum ∆p was recorded for a location where thePreston tube was in a laminar boundary layer and such data is only useful in a qualitativesense (see Section 2) For locations were the boundary layer is turbulent the minimum ∆pwas 340 Pa which gives a pressure scanner resolution of 06 The 249 kPa scanner wasused mainly to acquire the static pressures at the lateral ports

35 Data Acquisition Software

A software package called ImPressOne was used which communicates with the PSI 8400and displays and acquires the pressure data for the model under test For the staticpressure measurements 100 readings were acquired at each pressure port at a samplingrate of 20 Hz For the Preston-tube measurements the sample rate was increased and100 samples were acquired at each pressure port at a sampling rate of 50 Hz for eachfree-stream velocity

36 Experimental Procedure

The hull was tested with each of the selected tripping devices listed in Table 1 as wellas without a tripping device resulting in five different test configurations For each testconfiguration the static pressures were initially acquired for that particular configurationfollowed by the Preston-tube measurements

A Preston tube having a diameter of 06 mm was attached to the surface of the modelusing both plasticine and tape to ensure that the tube was positioned as flat as possibleon the surface of the model as shown in Figure 9 Preston-tube measurement were takenon the upper surface of the submarine model along a line directly above the centre-lineof the model For the dT = 02 and 05 mm wires and the grit case measurements weretaken from x = 73 mm to x = 1065 mm for a total of 18 stations For the dT = 01 mmwire measurements were limited to 3 stations between x = 305 mm and x = 442 mmThe stream-wise coordinates for the Preston tube measurements are given in the Table 2Data were acquired for a range of free-stream velocities from 40 to 70 ms in incrementsof 5 ms

For each nominal velocity the corresponding model Reynolds number was calcu-lated assuming standard temperature and atmospheric pressure conditions 20C and101 325 Pa respectively For each given test the temperature and static pressure of theair within the test section were logged and the air density and viscosity were calculatedTo account for daily variations in temperature and atmospheric pressure the freestream

12 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Flow direction

Figure 9 Preston tube located on the centre-line of the upper-surface of submarine

velocity was adjusted to ensure that the model Reynolds number remained constant foreach given nominal velocity condition as shown in Table 3

Table 2 Skin-friction measurement stations Where applicable the corresponding staticport number is given For the dT = 01 mm wire measurements were only taken at stations3050 3600 as well as an additional station at x = 4425 mm

xmm 731 787 843 900 1125 1350 1575 1800 2150Static port - - - 6 - 7 - 8 -

xmm 2500 3050 3600 5250 7000 8700 9500 10100 10650Static port 9 - 12 13 14 17 18 21 24

Table 3 Reynolds numbers (based on submarine length 135 m) corresponding to thenominal free-stream velocities

Nominal Uinfin 40 45 50 55 60 65 70 msRe 358 403 448 493 537 582 627 times106

37 Data Reduction

The static pressure readings from the pressure ports were converted to pressure coefficientsusing the relationship

Cp =ps minus pinfinpt minus pinfin

(11)

where pinfin is the reference free-stream static pressure pt is the reference free-stream totalpressure and ps is the static pressure on the surface of the submarine model

As explained in Section 34 all Preston tube pressures are measured relative to the free-stream static pressure In order to apply the Preston tube calibration (4)-(6) the loggedPreston-tube pressure differences (ie pp minus pinfin) must first be converted to a ∆p = pp minus ps

UNCLASSIFIED 13

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 9: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

Contents

Glossary xi

Notation xi

1 Introduction 1

11 Boundary-Layer Transition 1

12 Approach of Erm amp Joubert (1991) 2

13 Empirical Expressions to Determine Sizes of Tripping Devices 4

2 Preston-Tube Method of Measuring Skin-Friction Coefficients 4

3 Test Program 7

31 Test Facility 7

32 Test Model 7

33 Tripping Devices 10

34 Pressure Scanners 10

35 Data Acquisition Software 12

36 Experimental Procedure 12

37 Data Reduction 13

4 Results 14

41 Skin Friction Without a Tripping Device 14

42 Skin Friction With Tripping Devices 16

421 Comparison of the Different Trip Devices 21

422 Scaling of Skin Friction with Reynolds Number 22

423 Over-stimulation and the Maximum Trip Reynolds Number 23

43 Pressure Coefficients 24

44 Pressure Gradients 26

5 Comparison with CFD Predictions 29

6 Conclusions 30

7 Acknowledgements 32

Appendices

UNCLASSIFIED ix

DSTOndashTRndash2898 UNCLASSIFIED

A Summary of Tripping Devices Used in Previous Experiments 35

B Preston Tube Data Processing 36

C Skin Friction Coefficients 37

D Pressure Coefficients 45

x UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Glossary

DARPA Defense Advanced Research Projects AgencyCERP Corporate Enabling Research ProgramCFD Computational Fluid DynamicsLSWT Low-Speed Wind TunnelDSTO Defence Science and Technology Organisation

Notation

Cf Local skin-friction coefficientCp Pressure coefficientd Outer diameter of Preston tubedT Diameter of trip wireh Height of grit transition strippinfin Free-stream static pressurepp Total pressure of Preston tubeps Model surface static pressurept Free-stream total pressurep+x Non-dimensional pressure gradient parameterRe Reynolds numberRedT Reynolds number based on diameter of wireRex Reynolds number based on the stream-wise coordinateRext Streamwise Reynolds number of transition pointU Streamwise velocity in boundary layerU1 Streamwise velocity at edge of boundary layerUinfin Nominal streamwise velocity in tunnel working-sectionUτ Friction velocityw Width of grit transition stripx Streamwise coordinatext Streamwise coordinate of transition pointy Wall normal coordinate∆p ∆p = pp minus psν Kinematic viscosityρ Fluid densityτ0 Wall shear stress

UNCLASSIFIED xi

DSTOndashTRndash2898 UNCLASSIFIED

THIS PAGE IS INTENTIONALLY BLANK

xii UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

1 Introduction

This work aims to understand flow fields about a submarine As part of this programa series of experiments have been conducted in the Low-Speed Wind Tunnel (LSWT) atthe Defence Science and Technology Organisation (DSTO) to quantify the skin-frictiondistributions on a generic submarine model and in the process investigate the effectivenessof a limited range of tripping devices The results also provide a reference data set forcomputational fluid dynamics (CFD) validation of a submarine model

When conducting tests in wind tunnels on a sub-scale model for results of the exper-iment to be transferable to the full-scale vehicle the flow patterns and load coefficientson the model and the full-size vehicle need to be made similar Ideally this is achievedthrough matching the Reynolds number of the flow over the model to that of the full-scalevehicle However in practice this is difficult to achieve and is not always possible To en-sure that the flow features on the model are representative of those for the full-size vehiclea tripping device can be used such that the boundary layers (ie regions of laminar flowlaminar-to-turbulent transition and turbulent flow) are made similar However differenttripping devices can impart different disturbances into the flow In order to correctly stim-ulate the boundary layer on the submarine model and avoid over- or under-stimulationthe type and size of tripping devices need to be selected for a given Reynolds numberor Reynolds number range and also for a specific trip location Additionally the chosentripping device will be specific to a given tunnel and would be dependent on factors suchas the level of free-stream turbulence in the tunnel

dT

Ud

Trip wire

xd

Laminar Transition Turbulent

Boundary-layeredge

U1

Figure 1 Diagrammatic representation of a boundary layer being tripped based on adiagram given by White (1974)

11 Boundary-Layer Transition

Boundary-layer transition is a complicated physical process dependent on instability mech-anisms including Tollmien-Schlichting waves crossflow and Gortler instabilities (see Reedamp Saric 2008) Over the years there have been numerous articles published on transi-tion both from experimental investigations and CFD analyses in low-speed transonic

UNCLASSIFIED 1

DSTOndashTRndash2898 UNCLASSIFIED

and hypersonic flow regimes (for example Schlatter amp Henningson 2009) Details of thetransition process are still not fully understood In the present report transition physicalprocesses are not considered instead attention is focused on how to stabilise the posi-tion of the transition using a tripping device and to ensure that the turbulent boundarylayer is neither under- or over-stimulated irrespective of the flow physics associated withtransition

12 Approach of Erm amp Joubert (1991)

A diagrammatic representation of a boundary layer being tripped is shown in Figure 1where dT is the height of the tripping device U1 is the streamwise velocity at the edge ofthe boundary layer xd is the location of the tripping device measured from the nose ofthe model and Ud is the velocity in the boundary layer at the top of the device

A question that had to be addressed was what is the best size and type of trippingdevice to use in the current experiments in the LSWT to trip the boundary layer on thesubmarine model Erm amp Joubert (1991) faced a similar question in their studies on low-Reynolds-number flows over a smooth flat surface in a zero pressure gradient For differenttypes of tripping devices they measured longitudinal skin-friction coefficients for a rangeof free-stream velocities Their data for a 12 mm wire tripping device are reproduced inFigure 2 From this figure it can be seen that as the velocity is increased from 8 ms thedevice imparts an increased amount of turbulent energy into the flow so that the laminar-to-turbulent transition region moves upstream They conjectured that correct stimulationis associated with a particular curve when the peaks of successive curves correspondingto higher velocities do not advance significantly upstream Velocities lower than thatcorresponding to the particular curve were obviously associated with under-stimulatedflows since the peaks of the curves were well downstream of the device and thus thedevice was therefore not completely effective in tripping the flow Since the velocitycorresponding to the particular curve establishes a turbulent boundary layer almost to thepossible upstream limit of turbulent flow it seemed reasonable to assume that the maineffect of higher velocities was to overstimulate the flow

The x-coordinate corresponding to the peaks of Figure 2 are plotted in Figure 3 as afunction of streamwise velocity and it is apparent that the above condition for correct stim-ulation was satisfied when the velocity was between 10 and 12 ms This corresponds to aminimum Reynolds number of the tripping device in the range of RedT = U1dT ν = 800to 960 where ν is the kinematic viscosity For the case where a trip device has aReynolds number greater than the minimum required the tripping device may overstim-ulate the flow Note over-stimulation does not necessarily result in higher skin-frictionwhen compared to a correctly stimulated layer Rather it means that the disturbanceintroduced by the tripping device is felt downstream of the transition region and leadsto a ldquonon-standardrdquo turbulent boundary initially developing Ideally to assess whetherover-stimulation has occurred complete velocity profiles in the turbulent region need tobe measured and compared against reference data sets such as those collated by Coles(1962)

It should be noted that in the current work the boundary layer develops in a pressuregradient with wall curvature in both the streamwise and spanwise directions Whereas

2 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

the work of Erm amp Joubert (1991) was undertaken on a flat plate zero pressure gradientthis means the RedT values given above cannot be applied directly to predict the trip sizerequired However the approach taken here broadly follows that of Erm amp Joubert (1991)in that a range of trip Reynolds numbers were tested (by varying both freestream velocityand trip size) and the skin-friction downstream of the trip measured

0 01 02x (m)

03 04 05

Figure 2 Cf vs x measurements for a 12 mm diameter trip wire for different free-streamvelocities as obtained by Erm amp Joubert (1991)

8 9 10 11 12 13 14

xlocation

(m)of

peakCf

Location of peak Cf

Location of trip device

01

02

0

Uinfin (ms)

Figure 3 Location of the peak Cf values shown in Figure 2

UNCLASSIFIED 3

DSTOndashTRndash2898 UNCLASSIFIED

13 Empirical Expressions to Determine Sizes of TrippingDevices

Researchers have proposed different empirical expressions for determining the size of deviceto use to trip the flow The relationships incorporate parameters including the height ofthe tripping device dT the velocity at the edge of the boundary layer U1 the velocity inthe undisturbed boundary layer at the top of the device Ud and the wall friction velocityevaluated at the device Uτ The friction velocity is defined by τ0 = ρU2

τ where τ0 is thesurface shear stress and ρ is the fluid density Recommendations for fully-effective trippingcover quite a wide range Tani et al (1940) proposed the criterion UτdT ν = 13 Fage ampPreston (1941) proposed UτdT ν = 20 Braslow amp Knox (1958) proposed UddT ν = 600and Gibbings (1959) proposed U1dT ν = 826 It should be noted that the criterion ofGibbings (1959) is based on a review of many data sets included those of Tani amp Sato(1956) and Fage amp Preston (1941) Gibbings (1959) expresses the Tani amp Sato (1956)and Fage amp Preston (1941) criteria as Reynolds numbers based on the freestream velocitywhich gives values of U1dT ν = 600 and 840 respectively The criterion given aboverepresent minimum values of the tripping device Reynolds number required to correctlytrip the boundary layer and agree with the results of Erm amp Joubert (1991)

An analysis of the literature for tests done on bodies of revolution indicated that thereis no consistent approach for selecting the size and type of device to use on such bodiesAppendix A gives details of devices used by different investigators for bodies of revolutiontogether with other experimental information Based on the freestream velocity and tripheight the Reynolds numbers of the trip devices given in Appendix A range from 200 to40 times 103 For the present investigation the approach used to establish the effects thatdifferent devices had on tripping laminar boundary layers was similar to that used byErm amp Joubert (1991) for a smooth flat plate in a zero pressure gradient Using theirtechnique it is possible to establish the size and type of tripping device to be used for agiven velocity to obtain correctly stimulated turbulent boundary layers

2 Preston-Tube Method of Measuring

Skin-Friction Coefficients

Skin-friction coefficients in a turbulent boundary layer flowing over a smooth surface canbe measured in a number of different ways (Fernholz et al 1996) including using Prestontubes (Preston 1954) from velocity profiles and using devices mounted flush with thesurface of a model Of the alternative approaches the Preston-tube method is convenientand is widely used The method makes use of a simple Pitot tube placed on the surfaceof a body and when used this way it is termed a Preston tube The method depends onan underlining assumption that in the region adjacent to the surface the flow is primarilydetermined by the surface shear stress and the properties of the fluid and is independentof factors such as pressure gradient and surface curvature The assumption implies thatthe velocity profile in a turbulent boundary layer adjacent to the surface is given by

U

Uτ= f

(Uτy

ν

)(1)

4 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

where U is the local stream-wise velocity Uτ is the friction velocity f is a universalfunction y is the wall normal coordinate and ν is the kinematic viscosity Equation (1) isoften referred to as the ldquolaw of the wallrdquo (Coles 1956)

A Pitot tube placed on the wall will measure a pressure relative to the wall staticpressure of ∆p = ρU22 at an effective coordinate y = c0d where d is the outer diameterof the Pitot tube and c0 is an unknown constant Substituting the values U =

radic(2∆pρ)

and y = cod into (1) yields a relationship between the wall shear stress fluid propertiesPreston-tube pressure difference and the tube diameter which is given by

2∆p

ρUτ2 =

[f

(Uτ c0d

ν

)]2 (2)

Alternatively for the purpose of measuring skin friction (2) can be expressed more con-veniently in the form

τ0d2

4ρν2= F

(∆pd2

4ρν2

)(3)

where c0 has been absorbed into the function F The function F represents the ldquocalibra-tionrdquo function for a Preston tube and several experimentally derived forms exist in theliterature (see Preston 1954 Patel 1965 Zagarola et al 2001) Generally the calibrationis determined by placing the Preston tube in a pipe flow where the wall shear stress (orfriction factor) can be determined accurately by measuring the pressure gradient in thepipe

For the data presented in this report the calibration of Patel (1965) was used todetermine the wall shear stress The calibration curve of Patel (1965) is given as follows

xlowast =ylowast + 2 log10(195ylowast + 410) for 55 ltUτd

2νlt 800 (4)

ylowast =08287 minus 01381xlowast + 01437xlowast2 minus 0006xlowast3 for 56 ltUτd

2νlt 55 and (5)

ylowast =1

2xlowast + 0037 for

Uτd

2νlt 56 (6)

where

xlowast = log10

(∆pd2

4ρν2

)and ylowast = log10

(τ0d

2

4ρν2

)

The local skin friction coefficient Cf is then found using

Cf =τ0

12ρU

21

(7)

where U1 is the streamwise velocity at the edge of the boundary layer

The calibration given by (4)-(6) is valid only for a hydrodynamically smooth surfaceA surface is considered hydrodynamically smooth provided that the height of surfaceroughness elements remain less than 5νUτ (Jimenez 2004) The minimum value of 5νUτthat was measured was approximately 4microm and the measured surface finish was found tobe an order of magnitude less than this value (Section 32) Hence the requirement of ahydrodynamically smooth surface is satisfied for this experiment

UNCLASSIFIED 5

DSTOndashTRndash2898 UNCLASSIFIED

The fundamental requirement for using a Preston tube is that the boundary layer isin a turbulent state and that the dimension of the Preston tube is such that it remainswithin the region where (1) is valid (ie from (4) Uτdν lt 1600) The diameter of thePreston tube for all experiments was d = 06 mm and this ensured that Uτdν remainedless than 1600 well within the range of the calibration (4)

It is known that for sufficiently strong pressure gradients the form of (1) changes (seeNickels 2004) Patel (1965) quantifies the effect of pressure gradients using the non-dimensional pressure gradient parameter1

p+x =ν

ρU3τ

dp

dx (8)

The error associated with using a Preston tube in pressure gradients is quantified by Patel(1965) and is given by the following inequalities

1 Adverse pressure gradient

Max Error 3 0 lt p+x lt 001 andUτd

νle 200 (9a)

Max Error 6 0 lt p+x lt 0015 andUτd

νle 250 (9b)

2 Favourable pressure gradient

Max Error 3 minus0005 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10a)

Max Error 6 minus0007 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10b)

The pressure gradient data are presented in Section 44 and were found to fall within thelimits of (9a) and (10a) indicating that the skin-friction coefficients are valid to withinplusmn3 This accuracy is similar to the alternative direct skin-friction measuring techniqueswhich typically achieve an accuracy of plusmn4 (Fernholz et al 1996)

The effect of model spanwise curvature on (4)-(6) is not quantified A reasonableassumption is that since the boundary layer thickness is much less than the model diameterthe effect of spanwise model curvature can be neglected

The Preston-tube method as outlined above requires that the boundary layer is in aturbulent state For this reason the method cannot be used to infer the skin friction atlocations were the boundary layer is in a laminar state However the ∆p values read by thePreston tube can be used to determine where laminar-to-turbulent transition occurs Theregion of transition is associated with a discontinuity in ∆p when plotted as a functionof streamwise coordinate x as shown by Erm amp Joubert (1991)

1for clarity we have adopted the notation for the pressure gradient parameter used by Nickels (2004)Patel (1965) uses the symbol ∆

6 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 4 LSWT Layout see Erm (2003)

3 Test Program

In this preliminary investigation four different tripping devices were used to investigatethe effect of the device on the skin-friction profile of a generic sub-scale submarine modelTests were conducted both with and without the tripping devices at a range of nominalfree-stream velocities Uinfin ranging from Uinfin = 40 to 70 ms to assess their effectivenessin tripping the boundary layer

31 Test Facility

The Low-Speed Wind Tunnel at DSTO is a closed circuit continuous flow tunnel with acontraction ratio of 41 The test section has an irregular octagonal shape with a heightof 213 m a width of 274 m and a length of 6553 m with a longitudinal turbulenceintensity of approximately 04 in the region where the models are tested (see Erm2003) An outline of the plan of the wind tunnel is shown in Figure 4 Free-streamvelocities were measured using static pressure rings at the upstream and downstreamends of the contraction A Pitot-static probe mounted on the side wall near the front ofthe working section was used to provide an independent measurement of the free-streamvelocity

32 Test Model

The sub-scale submarine model utilised in these tests is referred to as the Joubert modelsince the geometry is based on the work of Joubert (2004) and Joubert (2006) as well asLoid amp Bystrom (1983) The model was designed for the purpose of experimental and

UNCLASSIFIED 7

DSTOndashTRndash2898 UNCLASSIFIED

1

2 345

6 7 8 91011

12 13 141516

17 181920

212223

24 252627

28 29 303132

33 34

35

Top view

Side view

Figure 5 Schematic of scale model showing static-pressure port locations green and redmarkers represent the starboard and port static-pressure ports respectively

numerical studies and has no full-scale equivalent While the full model includes a casingcentre fin and control surfaces all tests reported here were conducted on the axisymmetricbody shape only

The model was machined from aluminum and consists of an ellipsoidal nose a cylin-drical centre-body and a streamlined tail section At the design stage an N6 surface finishwas specified for the model which corresponds to a roughness of 08microm in waviness Af-ter manufacture the surface finish was checked using a Surface Roughness Indicator andthe finish was found to be better than the design specification The model was anodisedwhich increased the thickness of the natural oxide layer by about 10microm

The model is 1350 mm long with a maximum diameter of 185 mm and slendernessratio of 73 where the slenderness ratio is defined as hull length divided by maximumhull diameter The model contains 21 longitudinal static-pressure ports on the centre-lineof the upper surface and 14 lateral static-pressure ports offset to the port and starboardsides of the upper surface centre-line Figure 5 shows the stream-wise location of thestatic-pressure ports

The model was supported by a single pylon as shown in Figure 6 All tests were carriedout at zero angle of yaw and zero angle of pitch The origin of the body coordinate systemis located at the nose of the submarine model The x-axis corresponds to the axis ofsymmetry of the model

8 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 6 Submarine model mounted in LSWT showing pylon support and pitch controlarm

UNCLASSIFIED 9

DSTOndashTRndash2898 UNCLASSIFIED

Table 1 Details of tripping devices where the Reynolds number is based on the height ofthe device The minimum Reynolds number and maximum Reynolds number correspondto nominal freestream velocities of Uinfin = 40 ms and Uinfin = 70 ms respectively where his the height of the grit and w is the width of the grit

Device Dimensions (mm) RedT (min) RedT (max)

Wire 1 dT = 01 281 496Wire 2 dT = 02 577 1015Wire 3 dT = 05 1443 256680 Grit h = 021 w = 3 605 1073

33 Tripping Devices

In this work four tripping devices were tested and consisted of circular wires with diame-ters dT = 01 02 and 05 mm as well as a distributed silicon carbide grit of size 80 havinga width of 3 mm The circular wires were bent to conform to the local diameter of thesubmarine and then attached with ldquosuper-gluerdquo such that there was no gap between thewire and the model surface Figure 7 The silicon carbide grit is prepared by distributinga layer of grit on double-sided sticky tape the tape is then adhered to the submarineFigure 8 The tripping devices were attached to the submarine model circumferentiallylocated at a streamwise coordinate of x = 675 mm measured from the nose of the sub-marine which corresponds to 5 of the total model length The dimensions of the tripdevices along with the Reynolds number range of the trip devices are summarised inTable 1 Note that the Reynolds number of the trip device is defined as RedT = U1dT νwhere for the case of the 80 grit dT is replaced by the grit height h

34 Pressure Scanners

Pressure Systems Incorporated (PSI) brand pressure scanners were used to measure allstatic and total pressures The pressure scanners are differential pressure measurementunits consisting of an array of silicon piezoresistive pressure sensors one for each pressureport The outputs of the sensors are electronically multiplexed through a single on-boardinstrumentation amplifier using binary addressing The scanners include a two-positioncalibration manifold actuated by momentary pulses of control pressures In the calibrateposition all sensors are connected to a common calibration pressure port A series ofaccurately-measured pressures is applied through this port to characterize the sensorsProper and periodic on-line calibration maintains static errors within plusmn003 or betterof the full-scale pressure range

The pressure scanners are controlled and sampled using a PSI 8400 electronic measure-ment system It is a modular parallel processing system for high-speed pressure scanningat up to 20000 measurements per second and allows the use of digitally temperaturecompensated pressure scanners

Two differential pressure scanners were used in the experiments All pressures aremeasured relative to the free-stream static pressure pinfin as measured by the referencefree-stream Pitot-static probe Each pressure scanner contained 32 ports The full-scale

10 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 7 Location of trip wire

Figure 8 Photo showing the 3 mm wide band of 80 grit transition strip

UNCLASSIFIED 11

DSTOndashTRndash2898 UNCLASSIFIED

pressure range of the scanners is 249 kPa (ldquo10 inches-of-water scannerrdquo) and 689 kPa(ldquo1 psi scannerrdquo) The 689 kPa scanner was used to read the static pressure at the longi-tudinal ports as well as the output from the Preston tube and the Pitot-static probe

For the purpose of cross-checking and for redundancy the Preston tube was connectedto two independent ports of the 689 kPa scanner and the two readings averaged For thisscanner pressures could be read to an accuracy of 6890 times 00003 Pa ie about 2 Pa Theminimum ∆p measured by the Preston tube was 145 Pa which gives a pressure scannerresolution of 14 However this minimum ∆p was recorded for a location where thePreston tube was in a laminar boundary layer and such data is only useful in a qualitativesense (see Section 2) For locations were the boundary layer is turbulent the minimum ∆pwas 340 Pa which gives a pressure scanner resolution of 06 The 249 kPa scanner wasused mainly to acquire the static pressures at the lateral ports

35 Data Acquisition Software

A software package called ImPressOne was used which communicates with the PSI 8400and displays and acquires the pressure data for the model under test For the staticpressure measurements 100 readings were acquired at each pressure port at a samplingrate of 20 Hz For the Preston-tube measurements the sample rate was increased and100 samples were acquired at each pressure port at a sampling rate of 50 Hz for eachfree-stream velocity

36 Experimental Procedure

The hull was tested with each of the selected tripping devices listed in Table 1 as wellas without a tripping device resulting in five different test configurations For each testconfiguration the static pressures were initially acquired for that particular configurationfollowed by the Preston-tube measurements

A Preston tube having a diameter of 06 mm was attached to the surface of the modelusing both plasticine and tape to ensure that the tube was positioned as flat as possibleon the surface of the model as shown in Figure 9 Preston-tube measurement were takenon the upper surface of the submarine model along a line directly above the centre-lineof the model For the dT = 02 and 05 mm wires and the grit case measurements weretaken from x = 73 mm to x = 1065 mm for a total of 18 stations For the dT = 01 mmwire measurements were limited to 3 stations between x = 305 mm and x = 442 mmThe stream-wise coordinates for the Preston tube measurements are given in the Table 2Data were acquired for a range of free-stream velocities from 40 to 70 ms in incrementsof 5 ms

For each nominal velocity the corresponding model Reynolds number was calcu-lated assuming standard temperature and atmospheric pressure conditions 20C and101 325 Pa respectively For each given test the temperature and static pressure of theair within the test section were logged and the air density and viscosity were calculatedTo account for daily variations in temperature and atmospheric pressure the freestream

12 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Flow direction

Figure 9 Preston tube located on the centre-line of the upper-surface of submarine

velocity was adjusted to ensure that the model Reynolds number remained constant foreach given nominal velocity condition as shown in Table 3

Table 2 Skin-friction measurement stations Where applicable the corresponding staticport number is given For the dT = 01 mm wire measurements were only taken at stations3050 3600 as well as an additional station at x = 4425 mm

xmm 731 787 843 900 1125 1350 1575 1800 2150Static port - - - 6 - 7 - 8 -

xmm 2500 3050 3600 5250 7000 8700 9500 10100 10650Static port 9 - 12 13 14 17 18 21 24

Table 3 Reynolds numbers (based on submarine length 135 m) corresponding to thenominal free-stream velocities

Nominal Uinfin 40 45 50 55 60 65 70 msRe 358 403 448 493 537 582 627 times106

37 Data Reduction

The static pressure readings from the pressure ports were converted to pressure coefficientsusing the relationship

Cp =ps minus pinfinpt minus pinfin

(11)

where pinfin is the reference free-stream static pressure pt is the reference free-stream totalpressure and ps is the static pressure on the surface of the submarine model

As explained in Section 34 all Preston tube pressures are measured relative to the free-stream static pressure In order to apply the Preston tube calibration (4)-(6) the loggedPreston-tube pressure differences (ie pp minus pinfin) must first be converted to a ∆p = pp minus ps

UNCLASSIFIED 13

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 10: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

A Summary of Tripping Devices Used in Previous Experiments 35

B Preston Tube Data Processing 36

C Skin Friction Coefficients 37

D Pressure Coefficients 45

x UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Glossary

DARPA Defense Advanced Research Projects AgencyCERP Corporate Enabling Research ProgramCFD Computational Fluid DynamicsLSWT Low-Speed Wind TunnelDSTO Defence Science and Technology Organisation

Notation

Cf Local skin-friction coefficientCp Pressure coefficientd Outer diameter of Preston tubedT Diameter of trip wireh Height of grit transition strippinfin Free-stream static pressurepp Total pressure of Preston tubeps Model surface static pressurept Free-stream total pressurep+x Non-dimensional pressure gradient parameterRe Reynolds numberRedT Reynolds number based on diameter of wireRex Reynolds number based on the stream-wise coordinateRext Streamwise Reynolds number of transition pointU Streamwise velocity in boundary layerU1 Streamwise velocity at edge of boundary layerUinfin Nominal streamwise velocity in tunnel working-sectionUτ Friction velocityw Width of grit transition stripx Streamwise coordinatext Streamwise coordinate of transition pointy Wall normal coordinate∆p ∆p = pp minus psν Kinematic viscosityρ Fluid densityτ0 Wall shear stress

UNCLASSIFIED xi

DSTOndashTRndash2898 UNCLASSIFIED

THIS PAGE IS INTENTIONALLY BLANK

xii UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

1 Introduction

This work aims to understand flow fields about a submarine As part of this programa series of experiments have been conducted in the Low-Speed Wind Tunnel (LSWT) atthe Defence Science and Technology Organisation (DSTO) to quantify the skin-frictiondistributions on a generic submarine model and in the process investigate the effectivenessof a limited range of tripping devices The results also provide a reference data set forcomputational fluid dynamics (CFD) validation of a submarine model

When conducting tests in wind tunnels on a sub-scale model for results of the exper-iment to be transferable to the full-scale vehicle the flow patterns and load coefficientson the model and the full-size vehicle need to be made similar Ideally this is achievedthrough matching the Reynolds number of the flow over the model to that of the full-scalevehicle However in practice this is difficult to achieve and is not always possible To en-sure that the flow features on the model are representative of those for the full-size vehiclea tripping device can be used such that the boundary layers (ie regions of laminar flowlaminar-to-turbulent transition and turbulent flow) are made similar However differenttripping devices can impart different disturbances into the flow In order to correctly stim-ulate the boundary layer on the submarine model and avoid over- or under-stimulationthe type and size of tripping devices need to be selected for a given Reynolds numberor Reynolds number range and also for a specific trip location Additionally the chosentripping device will be specific to a given tunnel and would be dependent on factors suchas the level of free-stream turbulence in the tunnel

dT

Ud

Trip wire

xd

Laminar Transition Turbulent

Boundary-layeredge

U1

Figure 1 Diagrammatic representation of a boundary layer being tripped based on adiagram given by White (1974)

11 Boundary-Layer Transition

Boundary-layer transition is a complicated physical process dependent on instability mech-anisms including Tollmien-Schlichting waves crossflow and Gortler instabilities (see Reedamp Saric 2008) Over the years there have been numerous articles published on transi-tion both from experimental investigations and CFD analyses in low-speed transonic

UNCLASSIFIED 1

DSTOndashTRndash2898 UNCLASSIFIED

and hypersonic flow regimes (for example Schlatter amp Henningson 2009) Details of thetransition process are still not fully understood In the present report transition physicalprocesses are not considered instead attention is focused on how to stabilise the posi-tion of the transition using a tripping device and to ensure that the turbulent boundarylayer is neither under- or over-stimulated irrespective of the flow physics associated withtransition

12 Approach of Erm amp Joubert (1991)

A diagrammatic representation of a boundary layer being tripped is shown in Figure 1where dT is the height of the tripping device U1 is the streamwise velocity at the edge ofthe boundary layer xd is the location of the tripping device measured from the nose ofthe model and Ud is the velocity in the boundary layer at the top of the device

A question that had to be addressed was what is the best size and type of trippingdevice to use in the current experiments in the LSWT to trip the boundary layer on thesubmarine model Erm amp Joubert (1991) faced a similar question in their studies on low-Reynolds-number flows over a smooth flat surface in a zero pressure gradient For differenttypes of tripping devices they measured longitudinal skin-friction coefficients for a rangeof free-stream velocities Their data for a 12 mm wire tripping device are reproduced inFigure 2 From this figure it can be seen that as the velocity is increased from 8 ms thedevice imparts an increased amount of turbulent energy into the flow so that the laminar-to-turbulent transition region moves upstream They conjectured that correct stimulationis associated with a particular curve when the peaks of successive curves correspondingto higher velocities do not advance significantly upstream Velocities lower than thatcorresponding to the particular curve were obviously associated with under-stimulatedflows since the peaks of the curves were well downstream of the device and thus thedevice was therefore not completely effective in tripping the flow Since the velocitycorresponding to the particular curve establishes a turbulent boundary layer almost to thepossible upstream limit of turbulent flow it seemed reasonable to assume that the maineffect of higher velocities was to overstimulate the flow

The x-coordinate corresponding to the peaks of Figure 2 are plotted in Figure 3 as afunction of streamwise velocity and it is apparent that the above condition for correct stim-ulation was satisfied when the velocity was between 10 and 12 ms This corresponds to aminimum Reynolds number of the tripping device in the range of RedT = U1dT ν = 800to 960 where ν is the kinematic viscosity For the case where a trip device has aReynolds number greater than the minimum required the tripping device may overstim-ulate the flow Note over-stimulation does not necessarily result in higher skin-frictionwhen compared to a correctly stimulated layer Rather it means that the disturbanceintroduced by the tripping device is felt downstream of the transition region and leadsto a ldquonon-standardrdquo turbulent boundary initially developing Ideally to assess whetherover-stimulation has occurred complete velocity profiles in the turbulent region need tobe measured and compared against reference data sets such as those collated by Coles(1962)

It should be noted that in the current work the boundary layer develops in a pressuregradient with wall curvature in both the streamwise and spanwise directions Whereas

2 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

the work of Erm amp Joubert (1991) was undertaken on a flat plate zero pressure gradientthis means the RedT values given above cannot be applied directly to predict the trip sizerequired However the approach taken here broadly follows that of Erm amp Joubert (1991)in that a range of trip Reynolds numbers were tested (by varying both freestream velocityand trip size) and the skin-friction downstream of the trip measured

0 01 02x (m)

03 04 05

Figure 2 Cf vs x measurements for a 12 mm diameter trip wire for different free-streamvelocities as obtained by Erm amp Joubert (1991)

8 9 10 11 12 13 14

xlocation

(m)of

peakCf

Location of peak Cf

Location of trip device

01

02

0

Uinfin (ms)

Figure 3 Location of the peak Cf values shown in Figure 2

UNCLASSIFIED 3

DSTOndashTRndash2898 UNCLASSIFIED

13 Empirical Expressions to Determine Sizes of TrippingDevices

Researchers have proposed different empirical expressions for determining the size of deviceto use to trip the flow The relationships incorporate parameters including the height ofthe tripping device dT the velocity at the edge of the boundary layer U1 the velocity inthe undisturbed boundary layer at the top of the device Ud and the wall friction velocityevaluated at the device Uτ The friction velocity is defined by τ0 = ρU2

τ where τ0 is thesurface shear stress and ρ is the fluid density Recommendations for fully-effective trippingcover quite a wide range Tani et al (1940) proposed the criterion UτdT ν = 13 Fage ampPreston (1941) proposed UτdT ν = 20 Braslow amp Knox (1958) proposed UddT ν = 600and Gibbings (1959) proposed U1dT ν = 826 It should be noted that the criterion ofGibbings (1959) is based on a review of many data sets included those of Tani amp Sato(1956) and Fage amp Preston (1941) Gibbings (1959) expresses the Tani amp Sato (1956)and Fage amp Preston (1941) criteria as Reynolds numbers based on the freestream velocitywhich gives values of U1dT ν = 600 and 840 respectively The criterion given aboverepresent minimum values of the tripping device Reynolds number required to correctlytrip the boundary layer and agree with the results of Erm amp Joubert (1991)

An analysis of the literature for tests done on bodies of revolution indicated that thereis no consistent approach for selecting the size and type of device to use on such bodiesAppendix A gives details of devices used by different investigators for bodies of revolutiontogether with other experimental information Based on the freestream velocity and tripheight the Reynolds numbers of the trip devices given in Appendix A range from 200 to40 times 103 For the present investigation the approach used to establish the effects thatdifferent devices had on tripping laminar boundary layers was similar to that used byErm amp Joubert (1991) for a smooth flat plate in a zero pressure gradient Using theirtechnique it is possible to establish the size and type of tripping device to be used for agiven velocity to obtain correctly stimulated turbulent boundary layers

2 Preston-Tube Method of Measuring

Skin-Friction Coefficients

Skin-friction coefficients in a turbulent boundary layer flowing over a smooth surface canbe measured in a number of different ways (Fernholz et al 1996) including using Prestontubes (Preston 1954) from velocity profiles and using devices mounted flush with thesurface of a model Of the alternative approaches the Preston-tube method is convenientand is widely used The method makes use of a simple Pitot tube placed on the surfaceof a body and when used this way it is termed a Preston tube The method depends onan underlining assumption that in the region adjacent to the surface the flow is primarilydetermined by the surface shear stress and the properties of the fluid and is independentof factors such as pressure gradient and surface curvature The assumption implies thatthe velocity profile in a turbulent boundary layer adjacent to the surface is given by

U

Uτ= f

(Uτy

ν

)(1)

4 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

where U is the local stream-wise velocity Uτ is the friction velocity f is a universalfunction y is the wall normal coordinate and ν is the kinematic viscosity Equation (1) isoften referred to as the ldquolaw of the wallrdquo (Coles 1956)

A Pitot tube placed on the wall will measure a pressure relative to the wall staticpressure of ∆p = ρU22 at an effective coordinate y = c0d where d is the outer diameterof the Pitot tube and c0 is an unknown constant Substituting the values U =

radic(2∆pρ)

and y = cod into (1) yields a relationship between the wall shear stress fluid propertiesPreston-tube pressure difference and the tube diameter which is given by

2∆p

ρUτ2 =

[f

(Uτ c0d

ν

)]2 (2)

Alternatively for the purpose of measuring skin friction (2) can be expressed more con-veniently in the form

τ0d2

4ρν2= F

(∆pd2

4ρν2

)(3)

where c0 has been absorbed into the function F The function F represents the ldquocalibra-tionrdquo function for a Preston tube and several experimentally derived forms exist in theliterature (see Preston 1954 Patel 1965 Zagarola et al 2001) Generally the calibrationis determined by placing the Preston tube in a pipe flow where the wall shear stress (orfriction factor) can be determined accurately by measuring the pressure gradient in thepipe

For the data presented in this report the calibration of Patel (1965) was used todetermine the wall shear stress The calibration curve of Patel (1965) is given as follows

xlowast =ylowast + 2 log10(195ylowast + 410) for 55 ltUτd

2νlt 800 (4)

ylowast =08287 minus 01381xlowast + 01437xlowast2 minus 0006xlowast3 for 56 ltUτd

2νlt 55 and (5)

ylowast =1

2xlowast + 0037 for

Uτd

2νlt 56 (6)

where

xlowast = log10

(∆pd2

4ρν2

)and ylowast = log10

(τ0d

2

4ρν2

)

The local skin friction coefficient Cf is then found using

Cf =τ0

12ρU

21

(7)

where U1 is the streamwise velocity at the edge of the boundary layer

The calibration given by (4)-(6) is valid only for a hydrodynamically smooth surfaceA surface is considered hydrodynamically smooth provided that the height of surfaceroughness elements remain less than 5νUτ (Jimenez 2004) The minimum value of 5νUτthat was measured was approximately 4microm and the measured surface finish was found tobe an order of magnitude less than this value (Section 32) Hence the requirement of ahydrodynamically smooth surface is satisfied for this experiment

UNCLASSIFIED 5

DSTOndashTRndash2898 UNCLASSIFIED

The fundamental requirement for using a Preston tube is that the boundary layer isin a turbulent state and that the dimension of the Preston tube is such that it remainswithin the region where (1) is valid (ie from (4) Uτdν lt 1600) The diameter of thePreston tube for all experiments was d = 06 mm and this ensured that Uτdν remainedless than 1600 well within the range of the calibration (4)

It is known that for sufficiently strong pressure gradients the form of (1) changes (seeNickels 2004) Patel (1965) quantifies the effect of pressure gradients using the non-dimensional pressure gradient parameter1

p+x =ν

ρU3τ

dp

dx (8)

The error associated with using a Preston tube in pressure gradients is quantified by Patel(1965) and is given by the following inequalities

1 Adverse pressure gradient

Max Error 3 0 lt p+x lt 001 andUτd

νle 200 (9a)

Max Error 6 0 lt p+x lt 0015 andUτd

νle 250 (9b)

2 Favourable pressure gradient

Max Error 3 minus0005 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10a)

Max Error 6 minus0007 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10b)

The pressure gradient data are presented in Section 44 and were found to fall within thelimits of (9a) and (10a) indicating that the skin-friction coefficients are valid to withinplusmn3 This accuracy is similar to the alternative direct skin-friction measuring techniqueswhich typically achieve an accuracy of plusmn4 (Fernholz et al 1996)

The effect of model spanwise curvature on (4)-(6) is not quantified A reasonableassumption is that since the boundary layer thickness is much less than the model diameterthe effect of spanwise model curvature can be neglected

The Preston-tube method as outlined above requires that the boundary layer is in aturbulent state For this reason the method cannot be used to infer the skin friction atlocations were the boundary layer is in a laminar state However the ∆p values read by thePreston tube can be used to determine where laminar-to-turbulent transition occurs Theregion of transition is associated with a discontinuity in ∆p when plotted as a functionof streamwise coordinate x as shown by Erm amp Joubert (1991)

1for clarity we have adopted the notation for the pressure gradient parameter used by Nickels (2004)Patel (1965) uses the symbol ∆

6 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 4 LSWT Layout see Erm (2003)

3 Test Program

In this preliminary investigation four different tripping devices were used to investigatethe effect of the device on the skin-friction profile of a generic sub-scale submarine modelTests were conducted both with and without the tripping devices at a range of nominalfree-stream velocities Uinfin ranging from Uinfin = 40 to 70 ms to assess their effectivenessin tripping the boundary layer

31 Test Facility

The Low-Speed Wind Tunnel at DSTO is a closed circuit continuous flow tunnel with acontraction ratio of 41 The test section has an irregular octagonal shape with a heightof 213 m a width of 274 m and a length of 6553 m with a longitudinal turbulenceintensity of approximately 04 in the region where the models are tested (see Erm2003) An outline of the plan of the wind tunnel is shown in Figure 4 Free-streamvelocities were measured using static pressure rings at the upstream and downstreamends of the contraction A Pitot-static probe mounted on the side wall near the front ofthe working section was used to provide an independent measurement of the free-streamvelocity

32 Test Model

The sub-scale submarine model utilised in these tests is referred to as the Joubert modelsince the geometry is based on the work of Joubert (2004) and Joubert (2006) as well asLoid amp Bystrom (1983) The model was designed for the purpose of experimental and

UNCLASSIFIED 7

DSTOndashTRndash2898 UNCLASSIFIED

1

2 345

6 7 8 91011

12 13 141516

17 181920

212223

24 252627

28 29 303132

33 34

35

Top view

Side view

Figure 5 Schematic of scale model showing static-pressure port locations green and redmarkers represent the starboard and port static-pressure ports respectively

numerical studies and has no full-scale equivalent While the full model includes a casingcentre fin and control surfaces all tests reported here were conducted on the axisymmetricbody shape only

The model was machined from aluminum and consists of an ellipsoidal nose a cylin-drical centre-body and a streamlined tail section At the design stage an N6 surface finishwas specified for the model which corresponds to a roughness of 08microm in waviness Af-ter manufacture the surface finish was checked using a Surface Roughness Indicator andthe finish was found to be better than the design specification The model was anodisedwhich increased the thickness of the natural oxide layer by about 10microm

The model is 1350 mm long with a maximum diameter of 185 mm and slendernessratio of 73 where the slenderness ratio is defined as hull length divided by maximumhull diameter The model contains 21 longitudinal static-pressure ports on the centre-lineof the upper surface and 14 lateral static-pressure ports offset to the port and starboardsides of the upper surface centre-line Figure 5 shows the stream-wise location of thestatic-pressure ports

The model was supported by a single pylon as shown in Figure 6 All tests were carriedout at zero angle of yaw and zero angle of pitch The origin of the body coordinate systemis located at the nose of the submarine model The x-axis corresponds to the axis ofsymmetry of the model

8 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 6 Submarine model mounted in LSWT showing pylon support and pitch controlarm

UNCLASSIFIED 9

DSTOndashTRndash2898 UNCLASSIFIED

Table 1 Details of tripping devices where the Reynolds number is based on the height ofthe device The minimum Reynolds number and maximum Reynolds number correspondto nominal freestream velocities of Uinfin = 40 ms and Uinfin = 70 ms respectively where his the height of the grit and w is the width of the grit

Device Dimensions (mm) RedT (min) RedT (max)

Wire 1 dT = 01 281 496Wire 2 dT = 02 577 1015Wire 3 dT = 05 1443 256680 Grit h = 021 w = 3 605 1073

33 Tripping Devices

In this work four tripping devices were tested and consisted of circular wires with diame-ters dT = 01 02 and 05 mm as well as a distributed silicon carbide grit of size 80 havinga width of 3 mm The circular wires were bent to conform to the local diameter of thesubmarine and then attached with ldquosuper-gluerdquo such that there was no gap between thewire and the model surface Figure 7 The silicon carbide grit is prepared by distributinga layer of grit on double-sided sticky tape the tape is then adhered to the submarineFigure 8 The tripping devices were attached to the submarine model circumferentiallylocated at a streamwise coordinate of x = 675 mm measured from the nose of the sub-marine which corresponds to 5 of the total model length The dimensions of the tripdevices along with the Reynolds number range of the trip devices are summarised inTable 1 Note that the Reynolds number of the trip device is defined as RedT = U1dT νwhere for the case of the 80 grit dT is replaced by the grit height h

34 Pressure Scanners

Pressure Systems Incorporated (PSI) brand pressure scanners were used to measure allstatic and total pressures The pressure scanners are differential pressure measurementunits consisting of an array of silicon piezoresistive pressure sensors one for each pressureport The outputs of the sensors are electronically multiplexed through a single on-boardinstrumentation amplifier using binary addressing The scanners include a two-positioncalibration manifold actuated by momentary pulses of control pressures In the calibrateposition all sensors are connected to a common calibration pressure port A series ofaccurately-measured pressures is applied through this port to characterize the sensorsProper and periodic on-line calibration maintains static errors within plusmn003 or betterof the full-scale pressure range

The pressure scanners are controlled and sampled using a PSI 8400 electronic measure-ment system It is a modular parallel processing system for high-speed pressure scanningat up to 20000 measurements per second and allows the use of digitally temperaturecompensated pressure scanners

Two differential pressure scanners were used in the experiments All pressures aremeasured relative to the free-stream static pressure pinfin as measured by the referencefree-stream Pitot-static probe Each pressure scanner contained 32 ports The full-scale

10 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 7 Location of trip wire

Figure 8 Photo showing the 3 mm wide band of 80 grit transition strip

UNCLASSIFIED 11

DSTOndashTRndash2898 UNCLASSIFIED

pressure range of the scanners is 249 kPa (ldquo10 inches-of-water scannerrdquo) and 689 kPa(ldquo1 psi scannerrdquo) The 689 kPa scanner was used to read the static pressure at the longi-tudinal ports as well as the output from the Preston tube and the Pitot-static probe

For the purpose of cross-checking and for redundancy the Preston tube was connectedto two independent ports of the 689 kPa scanner and the two readings averaged For thisscanner pressures could be read to an accuracy of 6890 times 00003 Pa ie about 2 Pa Theminimum ∆p measured by the Preston tube was 145 Pa which gives a pressure scannerresolution of 14 However this minimum ∆p was recorded for a location where thePreston tube was in a laminar boundary layer and such data is only useful in a qualitativesense (see Section 2) For locations were the boundary layer is turbulent the minimum ∆pwas 340 Pa which gives a pressure scanner resolution of 06 The 249 kPa scanner wasused mainly to acquire the static pressures at the lateral ports

35 Data Acquisition Software

A software package called ImPressOne was used which communicates with the PSI 8400and displays and acquires the pressure data for the model under test For the staticpressure measurements 100 readings were acquired at each pressure port at a samplingrate of 20 Hz For the Preston-tube measurements the sample rate was increased and100 samples were acquired at each pressure port at a sampling rate of 50 Hz for eachfree-stream velocity

36 Experimental Procedure

The hull was tested with each of the selected tripping devices listed in Table 1 as wellas without a tripping device resulting in five different test configurations For each testconfiguration the static pressures were initially acquired for that particular configurationfollowed by the Preston-tube measurements

A Preston tube having a diameter of 06 mm was attached to the surface of the modelusing both plasticine and tape to ensure that the tube was positioned as flat as possibleon the surface of the model as shown in Figure 9 Preston-tube measurement were takenon the upper surface of the submarine model along a line directly above the centre-lineof the model For the dT = 02 and 05 mm wires and the grit case measurements weretaken from x = 73 mm to x = 1065 mm for a total of 18 stations For the dT = 01 mmwire measurements were limited to 3 stations between x = 305 mm and x = 442 mmThe stream-wise coordinates for the Preston tube measurements are given in the Table 2Data were acquired for a range of free-stream velocities from 40 to 70 ms in incrementsof 5 ms

For each nominal velocity the corresponding model Reynolds number was calcu-lated assuming standard temperature and atmospheric pressure conditions 20C and101 325 Pa respectively For each given test the temperature and static pressure of theair within the test section were logged and the air density and viscosity were calculatedTo account for daily variations in temperature and atmospheric pressure the freestream

12 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Flow direction

Figure 9 Preston tube located on the centre-line of the upper-surface of submarine

velocity was adjusted to ensure that the model Reynolds number remained constant foreach given nominal velocity condition as shown in Table 3

Table 2 Skin-friction measurement stations Where applicable the corresponding staticport number is given For the dT = 01 mm wire measurements were only taken at stations3050 3600 as well as an additional station at x = 4425 mm

xmm 731 787 843 900 1125 1350 1575 1800 2150Static port - - - 6 - 7 - 8 -

xmm 2500 3050 3600 5250 7000 8700 9500 10100 10650Static port 9 - 12 13 14 17 18 21 24

Table 3 Reynolds numbers (based on submarine length 135 m) corresponding to thenominal free-stream velocities

Nominal Uinfin 40 45 50 55 60 65 70 msRe 358 403 448 493 537 582 627 times106

37 Data Reduction

The static pressure readings from the pressure ports were converted to pressure coefficientsusing the relationship

Cp =ps minus pinfinpt minus pinfin

(11)

where pinfin is the reference free-stream static pressure pt is the reference free-stream totalpressure and ps is the static pressure on the surface of the submarine model

As explained in Section 34 all Preston tube pressures are measured relative to the free-stream static pressure In order to apply the Preston tube calibration (4)-(6) the loggedPreston-tube pressure differences (ie pp minus pinfin) must first be converted to a ∆p = pp minus ps

UNCLASSIFIED 13

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

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5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 11: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

Glossary

DARPA Defense Advanced Research Projects AgencyCERP Corporate Enabling Research ProgramCFD Computational Fluid DynamicsLSWT Low-Speed Wind TunnelDSTO Defence Science and Technology Organisation

Notation

Cf Local skin-friction coefficientCp Pressure coefficientd Outer diameter of Preston tubedT Diameter of trip wireh Height of grit transition strippinfin Free-stream static pressurepp Total pressure of Preston tubeps Model surface static pressurept Free-stream total pressurep+x Non-dimensional pressure gradient parameterRe Reynolds numberRedT Reynolds number based on diameter of wireRex Reynolds number based on the stream-wise coordinateRext Streamwise Reynolds number of transition pointU Streamwise velocity in boundary layerU1 Streamwise velocity at edge of boundary layerUinfin Nominal streamwise velocity in tunnel working-sectionUτ Friction velocityw Width of grit transition stripx Streamwise coordinatext Streamwise coordinate of transition pointy Wall normal coordinate∆p ∆p = pp minus psν Kinematic viscosityρ Fluid densityτ0 Wall shear stress

UNCLASSIFIED xi

DSTOndashTRndash2898 UNCLASSIFIED

THIS PAGE IS INTENTIONALLY BLANK

xii UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

1 Introduction

This work aims to understand flow fields about a submarine As part of this programa series of experiments have been conducted in the Low-Speed Wind Tunnel (LSWT) atthe Defence Science and Technology Organisation (DSTO) to quantify the skin-frictiondistributions on a generic submarine model and in the process investigate the effectivenessof a limited range of tripping devices The results also provide a reference data set forcomputational fluid dynamics (CFD) validation of a submarine model

When conducting tests in wind tunnels on a sub-scale model for results of the exper-iment to be transferable to the full-scale vehicle the flow patterns and load coefficientson the model and the full-size vehicle need to be made similar Ideally this is achievedthrough matching the Reynolds number of the flow over the model to that of the full-scalevehicle However in practice this is difficult to achieve and is not always possible To en-sure that the flow features on the model are representative of those for the full-size vehiclea tripping device can be used such that the boundary layers (ie regions of laminar flowlaminar-to-turbulent transition and turbulent flow) are made similar However differenttripping devices can impart different disturbances into the flow In order to correctly stim-ulate the boundary layer on the submarine model and avoid over- or under-stimulationthe type and size of tripping devices need to be selected for a given Reynolds numberor Reynolds number range and also for a specific trip location Additionally the chosentripping device will be specific to a given tunnel and would be dependent on factors suchas the level of free-stream turbulence in the tunnel

dT

Ud

Trip wire

xd

Laminar Transition Turbulent

Boundary-layeredge

U1

Figure 1 Diagrammatic representation of a boundary layer being tripped based on adiagram given by White (1974)

11 Boundary-Layer Transition

Boundary-layer transition is a complicated physical process dependent on instability mech-anisms including Tollmien-Schlichting waves crossflow and Gortler instabilities (see Reedamp Saric 2008) Over the years there have been numerous articles published on transi-tion both from experimental investigations and CFD analyses in low-speed transonic

UNCLASSIFIED 1

DSTOndashTRndash2898 UNCLASSIFIED

and hypersonic flow regimes (for example Schlatter amp Henningson 2009) Details of thetransition process are still not fully understood In the present report transition physicalprocesses are not considered instead attention is focused on how to stabilise the posi-tion of the transition using a tripping device and to ensure that the turbulent boundarylayer is neither under- or over-stimulated irrespective of the flow physics associated withtransition

12 Approach of Erm amp Joubert (1991)

A diagrammatic representation of a boundary layer being tripped is shown in Figure 1where dT is the height of the tripping device U1 is the streamwise velocity at the edge ofthe boundary layer xd is the location of the tripping device measured from the nose ofthe model and Ud is the velocity in the boundary layer at the top of the device

A question that had to be addressed was what is the best size and type of trippingdevice to use in the current experiments in the LSWT to trip the boundary layer on thesubmarine model Erm amp Joubert (1991) faced a similar question in their studies on low-Reynolds-number flows over a smooth flat surface in a zero pressure gradient For differenttypes of tripping devices they measured longitudinal skin-friction coefficients for a rangeof free-stream velocities Their data for a 12 mm wire tripping device are reproduced inFigure 2 From this figure it can be seen that as the velocity is increased from 8 ms thedevice imparts an increased amount of turbulent energy into the flow so that the laminar-to-turbulent transition region moves upstream They conjectured that correct stimulationis associated with a particular curve when the peaks of successive curves correspondingto higher velocities do not advance significantly upstream Velocities lower than thatcorresponding to the particular curve were obviously associated with under-stimulatedflows since the peaks of the curves were well downstream of the device and thus thedevice was therefore not completely effective in tripping the flow Since the velocitycorresponding to the particular curve establishes a turbulent boundary layer almost to thepossible upstream limit of turbulent flow it seemed reasonable to assume that the maineffect of higher velocities was to overstimulate the flow

The x-coordinate corresponding to the peaks of Figure 2 are plotted in Figure 3 as afunction of streamwise velocity and it is apparent that the above condition for correct stim-ulation was satisfied when the velocity was between 10 and 12 ms This corresponds to aminimum Reynolds number of the tripping device in the range of RedT = U1dT ν = 800to 960 where ν is the kinematic viscosity For the case where a trip device has aReynolds number greater than the minimum required the tripping device may overstim-ulate the flow Note over-stimulation does not necessarily result in higher skin-frictionwhen compared to a correctly stimulated layer Rather it means that the disturbanceintroduced by the tripping device is felt downstream of the transition region and leadsto a ldquonon-standardrdquo turbulent boundary initially developing Ideally to assess whetherover-stimulation has occurred complete velocity profiles in the turbulent region need tobe measured and compared against reference data sets such as those collated by Coles(1962)

It should be noted that in the current work the boundary layer develops in a pressuregradient with wall curvature in both the streamwise and spanwise directions Whereas

2 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

the work of Erm amp Joubert (1991) was undertaken on a flat plate zero pressure gradientthis means the RedT values given above cannot be applied directly to predict the trip sizerequired However the approach taken here broadly follows that of Erm amp Joubert (1991)in that a range of trip Reynolds numbers were tested (by varying both freestream velocityand trip size) and the skin-friction downstream of the trip measured

0 01 02x (m)

03 04 05

Figure 2 Cf vs x measurements for a 12 mm diameter trip wire for different free-streamvelocities as obtained by Erm amp Joubert (1991)

8 9 10 11 12 13 14

xlocation

(m)of

peakCf

Location of peak Cf

Location of trip device

01

02

0

Uinfin (ms)

Figure 3 Location of the peak Cf values shown in Figure 2

UNCLASSIFIED 3

DSTOndashTRndash2898 UNCLASSIFIED

13 Empirical Expressions to Determine Sizes of TrippingDevices

Researchers have proposed different empirical expressions for determining the size of deviceto use to trip the flow The relationships incorporate parameters including the height ofthe tripping device dT the velocity at the edge of the boundary layer U1 the velocity inthe undisturbed boundary layer at the top of the device Ud and the wall friction velocityevaluated at the device Uτ The friction velocity is defined by τ0 = ρU2

τ where τ0 is thesurface shear stress and ρ is the fluid density Recommendations for fully-effective trippingcover quite a wide range Tani et al (1940) proposed the criterion UτdT ν = 13 Fage ampPreston (1941) proposed UτdT ν = 20 Braslow amp Knox (1958) proposed UddT ν = 600and Gibbings (1959) proposed U1dT ν = 826 It should be noted that the criterion ofGibbings (1959) is based on a review of many data sets included those of Tani amp Sato(1956) and Fage amp Preston (1941) Gibbings (1959) expresses the Tani amp Sato (1956)and Fage amp Preston (1941) criteria as Reynolds numbers based on the freestream velocitywhich gives values of U1dT ν = 600 and 840 respectively The criterion given aboverepresent minimum values of the tripping device Reynolds number required to correctlytrip the boundary layer and agree with the results of Erm amp Joubert (1991)

An analysis of the literature for tests done on bodies of revolution indicated that thereis no consistent approach for selecting the size and type of device to use on such bodiesAppendix A gives details of devices used by different investigators for bodies of revolutiontogether with other experimental information Based on the freestream velocity and tripheight the Reynolds numbers of the trip devices given in Appendix A range from 200 to40 times 103 For the present investigation the approach used to establish the effects thatdifferent devices had on tripping laminar boundary layers was similar to that used byErm amp Joubert (1991) for a smooth flat plate in a zero pressure gradient Using theirtechnique it is possible to establish the size and type of tripping device to be used for agiven velocity to obtain correctly stimulated turbulent boundary layers

2 Preston-Tube Method of Measuring

Skin-Friction Coefficients

Skin-friction coefficients in a turbulent boundary layer flowing over a smooth surface canbe measured in a number of different ways (Fernholz et al 1996) including using Prestontubes (Preston 1954) from velocity profiles and using devices mounted flush with thesurface of a model Of the alternative approaches the Preston-tube method is convenientand is widely used The method makes use of a simple Pitot tube placed on the surfaceof a body and when used this way it is termed a Preston tube The method depends onan underlining assumption that in the region adjacent to the surface the flow is primarilydetermined by the surface shear stress and the properties of the fluid and is independentof factors such as pressure gradient and surface curvature The assumption implies thatthe velocity profile in a turbulent boundary layer adjacent to the surface is given by

U

Uτ= f

(Uτy

ν

)(1)

4 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

where U is the local stream-wise velocity Uτ is the friction velocity f is a universalfunction y is the wall normal coordinate and ν is the kinematic viscosity Equation (1) isoften referred to as the ldquolaw of the wallrdquo (Coles 1956)

A Pitot tube placed on the wall will measure a pressure relative to the wall staticpressure of ∆p = ρU22 at an effective coordinate y = c0d where d is the outer diameterof the Pitot tube and c0 is an unknown constant Substituting the values U =

radic(2∆pρ)

and y = cod into (1) yields a relationship between the wall shear stress fluid propertiesPreston-tube pressure difference and the tube diameter which is given by

2∆p

ρUτ2 =

[f

(Uτ c0d

ν

)]2 (2)

Alternatively for the purpose of measuring skin friction (2) can be expressed more con-veniently in the form

τ0d2

4ρν2= F

(∆pd2

4ρν2

)(3)

where c0 has been absorbed into the function F The function F represents the ldquocalibra-tionrdquo function for a Preston tube and several experimentally derived forms exist in theliterature (see Preston 1954 Patel 1965 Zagarola et al 2001) Generally the calibrationis determined by placing the Preston tube in a pipe flow where the wall shear stress (orfriction factor) can be determined accurately by measuring the pressure gradient in thepipe

For the data presented in this report the calibration of Patel (1965) was used todetermine the wall shear stress The calibration curve of Patel (1965) is given as follows

xlowast =ylowast + 2 log10(195ylowast + 410) for 55 ltUτd

2νlt 800 (4)

ylowast =08287 minus 01381xlowast + 01437xlowast2 minus 0006xlowast3 for 56 ltUτd

2νlt 55 and (5)

ylowast =1

2xlowast + 0037 for

Uτd

2νlt 56 (6)

where

xlowast = log10

(∆pd2

4ρν2

)and ylowast = log10

(τ0d

2

4ρν2

)

The local skin friction coefficient Cf is then found using

Cf =τ0

12ρU

21

(7)

where U1 is the streamwise velocity at the edge of the boundary layer

The calibration given by (4)-(6) is valid only for a hydrodynamically smooth surfaceA surface is considered hydrodynamically smooth provided that the height of surfaceroughness elements remain less than 5νUτ (Jimenez 2004) The minimum value of 5νUτthat was measured was approximately 4microm and the measured surface finish was found tobe an order of magnitude less than this value (Section 32) Hence the requirement of ahydrodynamically smooth surface is satisfied for this experiment

UNCLASSIFIED 5

DSTOndashTRndash2898 UNCLASSIFIED

The fundamental requirement for using a Preston tube is that the boundary layer isin a turbulent state and that the dimension of the Preston tube is such that it remainswithin the region where (1) is valid (ie from (4) Uτdν lt 1600) The diameter of thePreston tube for all experiments was d = 06 mm and this ensured that Uτdν remainedless than 1600 well within the range of the calibration (4)

It is known that for sufficiently strong pressure gradients the form of (1) changes (seeNickels 2004) Patel (1965) quantifies the effect of pressure gradients using the non-dimensional pressure gradient parameter1

p+x =ν

ρU3τ

dp

dx (8)

The error associated with using a Preston tube in pressure gradients is quantified by Patel(1965) and is given by the following inequalities

1 Adverse pressure gradient

Max Error 3 0 lt p+x lt 001 andUτd

νle 200 (9a)

Max Error 6 0 lt p+x lt 0015 andUτd

νle 250 (9b)

2 Favourable pressure gradient

Max Error 3 minus0005 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10a)

Max Error 6 minus0007 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10b)

The pressure gradient data are presented in Section 44 and were found to fall within thelimits of (9a) and (10a) indicating that the skin-friction coefficients are valid to withinplusmn3 This accuracy is similar to the alternative direct skin-friction measuring techniqueswhich typically achieve an accuracy of plusmn4 (Fernholz et al 1996)

The effect of model spanwise curvature on (4)-(6) is not quantified A reasonableassumption is that since the boundary layer thickness is much less than the model diameterthe effect of spanwise model curvature can be neglected

The Preston-tube method as outlined above requires that the boundary layer is in aturbulent state For this reason the method cannot be used to infer the skin friction atlocations were the boundary layer is in a laminar state However the ∆p values read by thePreston tube can be used to determine where laminar-to-turbulent transition occurs Theregion of transition is associated with a discontinuity in ∆p when plotted as a functionof streamwise coordinate x as shown by Erm amp Joubert (1991)

1for clarity we have adopted the notation for the pressure gradient parameter used by Nickels (2004)Patel (1965) uses the symbol ∆

6 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 4 LSWT Layout see Erm (2003)

3 Test Program

In this preliminary investigation four different tripping devices were used to investigatethe effect of the device on the skin-friction profile of a generic sub-scale submarine modelTests were conducted both with and without the tripping devices at a range of nominalfree-stream velocities Uinfin ranging from Uinfin = 40 to 70 ms to assess their effectivenessin tripping the boundary layer

31 Test Facility

The Low-Speed Wind Tunnel at DSTO is a closed circuit continuous flow tunnel with acontraction ratio of 41 The test section has an irregular octagonal shape with a heightof 213 m a width of 274 m and a length of 6553 m with a longitudinal turbulenceintensity of approximately 04 in the region where the models are tested (see Erm2003) An outline of the plan of the wind tunnel is shown in Figure 4 Free-streamvelocities were measured using static pressure rings at the upstream and downstreamends of the contraction A Pitot-static probe mounted on the side wall near the front ofthe working section was used to provide an independent measurement of the free-streamvelocity

32 Test Model

The sub-scale submarine model utilised in these tests is referred to as the Joubert modelsince the geometry is based on the work of Joubert (2004) and Joubert (2006) as well asLoid amp Bystrom (1983) The model was designed for the purpose of experimental and

UNCLASSIFIED 7

DSTOndashTRndash2898 UNCLASSIFIED

1

2 345

6 7 8 91011

12 13 141516

17 181920

212223

24 252627

28 29 303132

33 34

35

Top view

Side view

Figure 5 Schematic of scale model showing static-pressure port locations green and redmarkers represent the starboard and port static-pressure ports respectively

numerical studies and has no full-scale equivalent While the full model includes a casingcentre fin and control surfaces all tests reported here were conducted on the axisymmetricbody shape only

The model was machined from aluminum and consists of an ellipsoidal nose a cylin-drical centre-body and a streamlined tail section At the design stage an N6 surface finishwas specified for the model which corresponds to a roughness of 08microm in waviness Af-ter manufacture the surface finish was checked using a Surface Roughness Indicator andthe finish was found to be better than the design specification The model was anodisedwhich increased the thickness of the natural oxide layer by about 10microm

The model is 1350 mm long with a maximum diameter of 185 mm and slendernessratio of 73 where the slenderness ratio is defined as hull length divided by maximumhull diameter The model contains 21 longitudinal static-pressure ports on the centre-lineof the upper surface and 14 lateral static-pressure ports offset to the port and starboardsides of the upper surface centre-line Figure 5 shows the stream-wise location of thestatic-pressure ports

The model was supported by a single pylon as shown in Figure 6 All tests were carriedout at zero angle of yaw and zero angle of pitch The origin of the body coordinate systemis located at the nose of the submarine model The x-axis corresponds to the axis ofsymmetry of the model

8 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 6 Submarine model mounted in LSWT showing pylon support and pitch controlarm

UNCLASSIFIED 9

DSTOndashTRndash2898 UNCLASSIFIED

Table 1 Details of tripping devices where the Reynolds number is based on the height ofthe device The minimum Reynolds number and maximum Reynolds number correspondto nominal freestream velocities of Uinfin = 40 ms and Uinfin = 70 ms respectively where his the height of the grit and w is the width of the grit

Device Dimensions (mm) RedT (min) RedT (max)

Wire 1 dT = 01 281 496Wire 2 dT = 02 577 1015Wire 3 dT = 05 1443 256680 Grit h = 021 w = 3 605 1073

33 Tripping Devices

In this work four tripping devices were tested and consisted of circular wires with diame-ters dT = 01 02 and 05 mm as well as a distributed silicon carbide grit of size 80 havinga width of 3 mm The circular wires were bent to conform to the local diameter of thesubmarine and then attached with ldquosuper-gluerdquo such that there was no gap between thewire and the model surface Figure 7 The silicon carbide grit is prepared by distributinga layer of grit on double-sided sticky tape the tape is then adhered to the submarineFigure 8 The tripping devices were attached to the submarine model circumferentiallylocated at a streamwise coordinate of x = 675 mm measured from the nose of the sub-marine which corresponds to 5 of the total model length The dimensions of the tripdevices along with the Reynolds number range of the trip devices are summarised inTable 1 Note that the Reynolds number of the trip device is defined as RedT = U1dT νwhere for the case of the 80 grit dT is replaced by the grit height h

34 Pressure Scanners

Pressure Systems Incorporated (PSI) brand pressure scanners were used to measure allstatic and total pressures The pressure scanners are differential pressure measurementunits consisting of an array of silicon piezoresistive pressure sensors one for each pressureport The outputs of the sensors are electronically multiplexed through a single on-boardinstrumentation amplifier using binary addressing The scanners include a two-positioncalibration manifold actuated by momentary pulses of control pressures In the calibrateposition all sensors are connected to a common calibration pressure port A series ofaccurately-measured pressures is applied through this port to characterize the sensorsProper and periodic on-line calibration maintains static errors within plusmn003 or betterof the full-scale pressure range

The pressure scanners are controlled and sampled using a PSI 8400 electronic measure-ment system It is a modular parallel processing system for high-speed pressure scanningat up to 20000 measurements per second and allows the use of digitally temperaturecompensated pressure scanners

Two differential pressure scanners were used in the experiments All pressures aremeasured relative to the free-stream static pressure pinfin as measured by the referencefree-stream Pitot-static probe Each pressure scanner contained 32 ports The full-scale

10 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 7 Location of trip wire

Figure 8 Photo showing the 3 mm wide band of 80 grit transition strip

UNCLASSIFIED 11

DSTOndashTRndash2898 UNCLASSIFIED

pressure range of the scanners is 249 kPa (ldquo10 inches-of-water scannerrdquo) and 689 kPa(ldquo1 psi scannerrdquo) The 689 kPa scanner was used to read the static pressure at the longi-tudinal ports as well as the output from the Preston tube and the Pitot-static probe

For the purpose of cross-checking and for redundancy the Preston tube was connectedto two independent ports of the 689 kPa scanner and the two readings averaged For thisscanner pressures could be read to an accuracy of 6890 times 00003 Pa ie about 2 Pa Theminimum ∆p measured by the Preston tube was 145 Pa which gives a pressure scannerresolution of 14 However this minimum ∆p was recorded for a location where thePreston tube was in a laminar boundary layer and such data is only useful in a qualitativesense (see Section 2) For locations were the boundary layer is turbulent the minimum ∆pwas 340 Pa which gives a pressure scanner resolution of 06 The 249 kPa scanner wasused mainly to acquire the static pressures at the lateral ports

35 Data Acquisition Software

A software package called ImPressOne was used which communicates with the PSI 8400and displays and acquires the pressure data for the model under test For the staticpressure measurements 100 readings were acquired at each pressure port at a samplingrate of 20 Hz For the Preston-tube measurements the sample rate was increased and100 samples were acquired at each pressure port at a sampling rate of 50 Hz for eachfree-stream velocity

36 Experimental Procedure

The hull was tested with each of the selected tripping devices listed in Table 1 as wellas without a tripping device resulting in five different test configurations For each testconfiguration the static pressures were initially acquired for that particular configurationfollowed by the Preston-tube measurements

A Preston tube having a diameter of 06 mm was attached to the surface of the modelusing both plasticine and tape to ensure that the tube was positioned as flat as possibleon the surface of the model as shown in Figure 9 Preston-tube measurement were takenon the upper surface of the submarine model along a line directly above the centre-lineof the model For the dT = 02 and 05 mm wires and the grit case measurements weretaken from x = 73 mm to x = 1065 mm for a total of 18 stations For the dT = 01 mmwire measurements were limited to 3 stations between x = 305 mm and x = 442 mmThe stream-wise coordinates for the Preston tube measurements are given in the Table 2Data were acquired for a range of free-stream velocities from 40 to 70 ms in incrementsof 5 ms

For each nominal velocity the corresponding model Reynolds number was calcu-lated assuming standard temperature and atmospheric pressure conditions 20C and101 325 Pa respectively For each given test the temperature and static pressure of theair within the test section were logged and the air density and viscosity were calculatedTo account for daily variations in temperature and atmospheric pressure the freestream

12 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Flow direction

Figure 9 Preston tube located on the centre-line of the upper-surface of submarine

velocity was adjusted to ensure that the model Reynolds number remained constant foreach given nominal velocity condition as shown in Table 3

Table 2 Skin-friction measurement stations Where applicable the corresponding staticport number is given For the dT = 01 mm wire measurements were only taken at stations3050 3600 as well as an additional station at x = 4425 mm

xmm 731 787 843 900 1125 1350 1575 1800 2150Static port - - - 6 - 7 - 8 -

xmm 2500 3050 3600 5250 7000 8700 9500 10100 10650Static port 9 - 12 13 14 17 18 21 24

Table 3 Reynolds numbers (based on submarine length 135 m) corresponding to thenominal free-stream velocities

Nominal Uinfin 40 45 50 55 60 65 70 msRe 358 403 448 493 537 582 627 times106

37 Data Reduction

The static pressure readings from the pressure ports were converted to pressure coefficientsusing the relationship

Cp =ps minus pinfinpt minus pinfin

(11)

where pinfin is the reference free-stream static pressure pt is the reference free-stream totalpressure and ps is the static pressure on the surface of the submarine model

As explained in Section 34 all Preston tube pressures are measured relative to the free-stream static pressure In order to apply the Preston tube calibration (4)-(6) the loggedPreston-tube pressure differences (ie pp minus pinfin) must first be converted to a ∆p = pp minus ps

UNCLASSIFIED 13

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

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ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

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LA

SS

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D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 12: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

THIS PAGE IS INTENTIONALLY BLANK

xii UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

1 Introduction

This work aims to understand flow fields about a submarine As part of this programa series of experiments have been conducted in the Low-Speed Wind Tunnel (LSWT) atthe Defence Science and Technology Organisation (DSTO) to quantify the skin-frictiondistributions on a generic submarine model and in the process investigate the effectivenessof a limited range of tripping devices The results also provide a reference data set forcomputational fluid dynamics (CFD) validation of a submarine model

When conducting tests in wind tunnels on a sub-scale model for results of the exper-iment to be transferable to the full-scale vehicle the flow patterns and load coefficientson the model and the full-size vehicle need to be made similar Ideally this is achievedthrough matching the Reynolds number of the flow over the model to that of the full-scalevehicle However in practice this is difficult to achieve and is not always possible To en-sure that the flow features on the model are representative of those for the full-size vehiclea tripping device can be used such that the boundary layers (ie regions of laminar flowlaminar-to-turbulent transition and turbulent flow) are made similar However differenttripping devices can impart different disturbances into the flow In order to correctly stim-ulate the boundary layer on the submarine model and avoid over- or under-stimulationthe type and size of tripping devices need to be selected for a given Reynolds numberor Reynolds number range and also for a specific trip location Additionally the chosentripping device will be specific to a given tunnel and would be dependent on factors suchas the level of free-stream turbulence in the tunnel

dT

Ud

Trip wire

xd

Laminar Transition Turbulent

Boundary-layeredge

U1

Figure 1 Diagrammatic representation of a boundary layer being tripped based on adiagram given by White (1974)

11 Boundary-Layer Transition

Boundary-layer transition is a complicated physical process dependent on instability mech-anisms including Tollmien-Schlichting waves crossflow and Gortler instabilities (see Reedamp Saric 2008) Over the years there have been numerous articles published on transi-tion both from experimental investigations and CFD analyses in low-speed transonic

UNCLASSIFIED 1

DSTOndashTRndash2898 UNCLASSIFIED

and hypersonic flow regimes (for example Schlatter amp Henningson 2009) Details of thetransition process are still not fully understood In the present report transition physicalprocesses are not considered instead attention is focused on how to stabilise the posi-tion of the transition using a tripping device and to ensure that the turbulent boundarylayer is neither under- or over-stimulated irrespective of the flow physics associated withtransition

12 Approach of Erm amp Joubert (1991)

A diagrammatic representation of a boundary layer being tripped is shown in Figure 1where dT is the height of the tripping device U1 is the streamwise velocity at the edge ofthe boundary layer xd is the location of the tripping device measured from the nose ofthe model and Ud is the velocity in the boundary layer at the top of the device

A question that had to be addressed was what is the best size and type of trippingdevice to use in the current experiments in the LSWT to trip the boundary layer on thesubmarine model Erm amp Joubert (1991) faced a similar question in their studies on low-Reynolds-number flows over a smooth flat surface in a zero pressure gradient For differenttypes of tripping devices they measured longitudinal skin-friction coefficients for a rangeof free-stream velocities Their data for a 12 mm wire tripping device are reproduced inFigure 2 From this figure it can be seen that as the velocity is increased from 8 ms thedevice imparts an increased amount of turbulent energy into the flow so that the laminar-to-turbulent transition region moves upstream They conjectured that correct stimulationis associated with a particular curve when the peaks of successive curves correspondingto higher velocities do not advance significantly upstream Velocities lower than thatcorresponding to the particular curve were obviously associated with under-stimulatedflows since the peaks of the curves were well downstream of the device and thus thedevice was therefore not completely effective in tripping the flow Since the velocitycorresponding to the particular curve establishes a turbulent boundary layer almost to thepossible upstream limit of turbulent flow it seemed reasonable to assume that the maineffect of higher velocities was to overstimulate the flow

The x-coordinate corresponding to the peaks of Figure 2 are plotted in Figure 3 as afunction of streamwise velocity and it is apparent that the above condition for correct stim-ulation was satisfied when the velocity was between 10 and 12 ms This corresponds to aminimum Reynolds number of the tripping device in the range of RedT = U1dT ν = 800to 960 where ν is the kinematic viscosity For the case where a trip device has aReynolds number greater than the minimum required the tripping device may overstim-ulate the flow Note over-stimulation does not necessarily result in higher skin-frictionwhen compared to a correctly stimulated layer Rather it means that the disturbanceintroduced by the tripping device is felt downstream of the transition region and leadsto a ldquonon-standardrdquo turbulent boundary initially developing Ideally to assess whetherover-stimulation has occurred complete velocity profiles in the turbulent region need tobe measured and compared against reference data sets such as those collated by Coles(1962)

It should be noted that in the current work the boundary layer develops in a pressuregradient with wall curvature in both the streamwise and spanwise directions Whereas

2 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

the work of Erm amp Joubert (1991) was undertaken on a flat plate zero pressure gradientthis means the RedT values given above cannot be applied directly to predict the trip sizerequired However the approach taken here broadly follows that of Erm amp Joubert (1991)in that a range of trip Reynolds numbers were tested (by varying both freestream velocityand trip size) and the skin-friction downstream of the trip measured

0 01 02x (m)

03 04 05

Figure 2 Cf vs x measurements for a 12 mm diameter trip wire for different free-streamvelocities as obtained by Erm amp Joubert (1991)

8 9 10 11 12 13 14

xlocation

(m)of

peakCf

Location of peak Cf

Location of trip device

01

02

0

Uinfin (ms)

Figure 3 Location of the peak Cf values shown in Figure 2

UNCLASSIFIED 3

DSTOndashTRndash2898 UNCLASSIFIED

13 Empirical Expressions to Determine Sizes of TrippingDevices

Researchers have proposed different empirical expressions for determining the size of deviceto use to trip the flow The relationships incorporate parameters including the height ofthe tripping device dT the velocity at the edge of the boundary layer U1 the velocity inthe undisturbed boundary layer at the top of the device Ud and the wall friction velocityevaluated at the device Uτ The friction velocity is defined by τ0 = ρU2

τ where τ0 is thesurface shear stress and ρ is the fluid density Recommendations for fully-effective trippingcover quite a wide range Tani et al (1940) proposed the criterion UτdT ν = 13 Fage ampPreston (1941) proposed UτdT ν = 20 Braslow amp Knox (1958) proposed UddT ν = 600and Gibbings (1959) proposed U1dT ν = 826 It should be noted that the criterion ofGibbings (1959) is based on a review of many data sets included those of Tani amp Sato(1956) and Fage amp Preston (1941) Gibbings (1959) expresses the Tani amp Sato (1956)and Fage amp Preston (1941) criteria as Reynolds numbers based on the freestream velocitywhich gives values of U1dT ν = 600 and 840 respectively The criterion given aboverepresent minimum values of the tripping device Reynolds number required to correctlytrip the boundary layer and agree with the results of Erm amp Joubert (1991)

An analysis of the literature for tests done on bodies of revolution indicated that thereis no consistent approach for selecting the size and type of device to use on such bodiesAppendix A gives details of devices used by different investigators for bodies of revolutiontogether with other experimental information Based on the freestream velocity and tripheight the Reynolds numbers of the trip devices given in Appendix A range from 200 to40 times 103 For the present investigation the approach used to establish the effects thatdifferent devices had on tripping laminar boundary layers was similar to that used byErm amp Joubert (1991) for a smooth flat plate in a zero pressure gradient Using theirtechnique it is possible to establish the size and type of tripping device to be used for agiven velocity to obtain correctly stimulated turbulent boundary layers

2 Preston-Tube Method of Measuring

Skin-Friction Coefficients

Skin-friction coefficients in a turbulent boundary layer flowing over a smooth surface canbe measured in a number of different ways (Fernholz et al 1996) including using Prestontubes (Preston 1954) from velocity profiles and using devices mounted flush with thesurface of a model Of the alternative approaches the Preston-tube method is convenientand is widely used The method makes use of a simple Pitot tube placed on the surfaceof a body and when used this way it is termed a Preston tube The method depends onan underlining assumption that in the region adjacent to the surface the flow is primarilydetermined by the surface shear stress and the properties of the fluid and is independentof factors such as pressure gradient and surface curvature The assumption implies thatthe velocity profile in a turbulent boundary layer adjacent to the surface is given by

U

Uτ= f

(Uτy

ν

)(1)

4 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

where U is the local stream-wise velocity Uτ is the friction velocity f is a universalfunction y is the wall normal coordinate and ν is the kinematic viscosity Equation (1) isoften referred to as the ldquolaw of the wallrdquo (Coles 1956)

A Pitot tube placed on the wall will measure a pressure relative to the wall staticpressure of ∆p = ρU22 at an effective coordinate y = c0d where d is the outer diameterof the Pitot tube and c0 is an unknown constant Substituting the values U =

radic(2∆pρ)

and y = cod into (1) yields a relationship between the wall shear stress fluid propertiesPreston-tube pressure difference and the tube diameter which is given by

2∆p

ρUτ2 =

[f

(Uτ c0d

ν

)]2 (2)

Alternatively for the purpose of measuring skin friction (2) can be expressed more con-veniently in the form

τ0d2

4ρν2= F

(∆pd2

4ρν2

)(3)

where c0 has been absorbed into the function F The function F represents the ldquocalibra-tionrdquo function for a Preston tube and several experimentally derived forms exist in theliterature (see Preston 1954 Patel 1965 Zagarola et al 2001) Generally the calibrationis determined by placing the Preston tube in a pipe flow where the wall shear stress (orfriction factor) can be determined accurately by measuring the pressure gradient in thepipe

For the data presented in this report the calibration of Patel (1965) was used todetermine the wall shear stress The calibration curve of Patel (1965) is given as follows

xlowast =ylowast + 2 log10(195ylowast + 410) for 55 ltUτd

2νlt 800 (4)

ylowast =08287 minus 01381xlowast + 01437xlowast2 minus 0006xlowast3 for 56 ltUτd

2νlt 55 and (5)

ylowast =1

2xlowast + 0037 for

Uτd

2νlt 56 (6)

where

xlowast = log10

(∆pd2

4ρν2

)and ylowast = log10

(τ0d

2

4ρν2

)

The local skin friction coefficient Cf is then found using

Cf =τ0

12ρU

21

(7)

where U1 is the streamwise velocity at the edge of the boundary layer

The calibration given by (4)-(6) is valid only for a hydrodynamically smooth surfaceA surface is considered hydrodynamically smooth provided that the height of surfaceroughness elements remain less than 5νUτ (Jimenez 2004) The minimum value of 5νUτthat was measured was approximately 4microm and the measured surface finish was found tobe an order of magnitude less than this value (Section 32) Hence the requirement of ahydrodynamically smooth surface is satisfied for this experiment

UNCLASSIFIED 5

DSTOndashTRndash2898 UNCLASSIFIED

The fundamental requirement for using a Preston tube is that the boundary layer isin a turbulent state and that the dimension of the Preston tube is such that it remainswithin the region where (1) is valid (ie from (4) Uτdν lt 1600) The diameter of thePreston tube for all experiments was d = 06 mm and this ensured that Uτdν remainedless than 1600 well within the range of the calibration (4)

It is known that for sufficiently strong pressure gradients the form of (1) changes (seeNickels 2004) Patel (1965) quantifies the effect of pressure gradients using the non-dimensional pressure gradient parameter1

p+x =ν

ρU3τ

dp

dx (8)

The error associated with using a Preston tube in pressure gradients is quantified by Patel(1965) and is given by the following inequalities

1 Adverse pressure gradient

Max Error 3 0 lt p+x lt 001 andUτd

νle 200 (9a)

Max Error 6 0 lt p+x lt 0015 andUτd

νle 250 (9b)

2 Favourable pressure gradient

Max Error 3 minus0005 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10a)

Max Error 6 minus0007 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10b)

The pressure gradient data are presented in Section 44 and were found to fall within thelimits of (9a) and (10a) indicating that the skin-friction coefficients are valid to withinplusmn3 This accuracy is similar to the alternative direct skin-friction measuring techniqueswhich typically achieve an accuracy of plusmn4 (Fernholz et al 1996)

The effect of model spanwise curvature on (4)-(6) is not quantified A reasonableassumption is that since the boundary layer thickness is much less than the model diameterthe effect of spanwise model curvature can be neglected

The Preston-tube method as outlined above requires that the boundary layer is in aturbulent state For this reason the method cannot be used to infer the skin friction atlocations were the boundary layer is in a laminar state However the ∆p values read by thePreston tube can be used to determine where laminar-to-turbulent transition occurs Theregion of transition is associated with a discontinuity in ∆p when plotted as a functionof streamwise coordinate x as shown by Erm amp Joubert (1991)

1for clarity we have adopted the notation for the pressure gradient parameter used by Nickels (2004)Patel (1965) uses the symbol ∆

6 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 4 LSWT Layout see Erm (2003)

3 Test Program

In this preliminary investigation four different tripping devices were used to investigatethe effect of the device on the skin-friction profile of a generic sub-scale submarine modelTests were conducted both with and without the tripping devices at a range of nominalfree-stream velocities Uinfin ranging from Uinfin = 40 to 70 ms to assess their effectivenessin tripping the boundary layer

31 Test Facility

The Low-Speed Wind Tunnel at DSTO is a closed circuit continuous flow tunnel with acontraction ratio of 41 The test section has an irregular octagonal shape with a heightof 213 m a width of 274 m and a length of 6553 m with a longitudinal turbulenceintensity of approximately 04 in the region where the models are tested (see Erm2003) An outline of the plan of the wind tunnel is shown in Figure 4 Free-streamvelocities were measured using static pressure rings at the upstream and downstreamends of the contraction A Pitot-static probe mounted on the side wall near the front ofthe working section was used to provide an independent measurement of the free-streamvelocity

32 Test Model

The sub-scale submarine model utilised in these tests is referred to as the Joubert modelsince the geometry is based on the work of Joubert (2004) and Joubert (2006) as well asLoid amp Bystrom (1983) The model was designed for the purpose of experimental and

UNCLASSIFIED 7

DSTOndashTRndash2898 UNCLASSIFIED

1

2 345

6 7 8 91011

12 13 141516

17 181920

212223

24 252627

28 29 303132

33 34

35

Top view

Side view

Figure 5 Schematic of scale model showing static-pressure port locations green and redmarkers represent the starboard and port static-pressure ports respectively

numerical studies and has no full-scale equivalent While the full model includes a casingcentre fin and control surfaces all tests reported here were conducted on the axisymmetricbody shape only

The model was machined from aluminum and consists of an ellipsoidal nose a cylin-drical centre-body and a streamlined tail section At the design stage an N6 surface finishwas specified for the model which corresponds to a roughness of 08microm in waviness Af-ter manufacture the surface finish was checked using a Surface Roughness Indicator andthe finish was found to be better than the design specification The model was anodisedwhich increased the thickness of the natural oxide layer by about 10microm

The model is 1350 mm long with a maximum diameter of 185 mm and slendernessratio of 73 where the slenderness ratio is defined as hull length divided by maximumhull diameter The model contains 21 longitudinal static-pressure ports on the centre-lineof the upper surface and 14 lateral static-pressure ports offset to the port and starboardsides of the upper surface centre-line Figure 5 shows the stream-wise location of thestatic-pressure ports

The model was supported by a single pylon as shown in Figure 6 All tests were carriedout at zero angle of yaw and zero angle of pitch The origin of the body coordinate systemis located at the nose of the submarine model The x-axis corresponds to the axis ofsymmetry of the model

8 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 6 Submarine model mounted in LSWT showing pylon support and pitch controlarm

UNCLASSIFIED 9

DSTOndashTRndash2898 UNCLASSIFIED

Table 1 Details of tripping devices where the Reynolds number is based on the height ofthe device The minimum Reynolds number and maximum Reynolds number correspondto nominal freestream velocities of Uinfin = 40 ms and Uinfin = 70 ms respectively where his the height of the grit and w is the width of the grit

Device Dimensions (mm) RedT (min) RedT (max)

Wire 1 dT = 01 281 496Wire 2 dT = 02 577 1015Wire 3 dT = 05 1443 256680 Grit h = 021 w = 3 605 1073

33 Tripping Devices

In this work four tripping devices were tested and consisted of circular wires with diame-ters dT = 01 02 and 05 mm as well as a distributed silicon carbide grit of size 80 havinga width of 3 mm The circular wires were bent to conform to the local diameter of thesubmarine and then attached with ldquosuper-gluerdquo such that there was no gap between thewire and the model surface Figure 7 The silicon carbide grit is prepared by distributinga layer of grit on double-sided sticky tape the tape is then adhered to the submarineFigure 8 The tripping devices were attached to the submarine model circumferentiallylocated at a streamwise coordinate of x = 675 mm measured from the nose of the sub-marine which corresponds to 5 of the total model length The dimensions of the tripdevices along with the Reynolds number range of the trip devices are summarised inTable 1 Note that the Reynolds number of the trip device is defined as RedT = U1dT νwhere for the case of the 80 grit dT is replaced by the grit height h

34 Pressure Scanners

Pressure Systems Incorporated (PSI) brand pressure scanners were used to measure allstatic and total pressures The pressure scanners are differential pressure measurementunits consisting of an array of silicon piezoresistive pressure sensors one for each pressureport The outputs of the sensors are electronically multiplexed through a single on-boardinstrumentation amplifier using binary addressing The scanners include a two-positioncalibration manifold actuated by momentary pulses of control pressures In the calibrateposition all sensors are connected to a common calibration pressure port A series ofaccurately-measured pressures is applied through this port to characterize the sensorsProper and periodic on-line calibration maintains static errors within plusmn003 or betterof the full-scale pressure range

The pressure scanners are controlled and sampled using a PSI 8400 electronic measure-ment system It is a modular parallel processing system for high-speed pressure scanningat up to 20000 measurements per second and allows the use of digitally temperaturecompensated pressure scanners

Two differential pressure scanners were used in the experiments All pressures aremeasured relative to the free-stream static pressure pinfin as measured by the referencefree-stream Pitot-static probe Each pressure scanner contained 32 ports The full-scale

10 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 7 Location of trip wire

Figure 8 Photo showing the 3 mm wide band of 80 grit transition strip

UNCLASSIFIED 11

DSTOndashTRndash2898 UNCLASSIFIED

pressure range of the scanners is 249 kPa (ldquo10 inches-of-water scannerrdquo) and 689 kPa(ldquo1 psi scannerrdquo) The 689 kPa scanner was used to read the static pressure at the longi-tudinal ports as well as the output from the Preston tube and the Pitot-static probe

For the purpose of cross-checking and for redundancy the Preston tube was connectedto two independent ports of the 689 kPa scanner and the two readings averaged For thisscanner pressures could be read to an accuracy of 6890 times 00003 Pa ie about 2 Pa Theminimum ∆p measured by the Preston tube was 145 Pa which gives a pressure scannerresolution of 14 However this minimum ∆p was recorded for a location where thePreston tube was in a laminar boundary layer and such data is only useful in a qualitativesense (see Section 2) For locations were the boundary layer is turbulent the minimum ∆pwas 340 Pa which gives a pressure scanner resolution of 06 The 249 kPa scanner wasused mainly to acquire the static pressures at the lateral ports

35 Data Acquisition Software

A software package called ImPressOne was used which communicates with the PSI 8400and displays and acquires the pressure data for the model under test For the staticpressure measurements 100 readings were acquired at each pressure port at a samplingrate of 20 Hz For the Preston-tube measurements the sample rate was increased and100 samples were acquired at each pressure port at a sampling rate of 50 Hz for eachfree-stream velocity

36 Experimental Procedure

The hull was tested with each of the selected tripping devices listed in Table 1 as wellas without a tripping device resulting in five different test configurations For each testconfiguration the static pressures were initially acquired for that particular configurationfollowed by the Preston-tube measurements

A Preston tube having a diameter of 06 mm was attached to the surface of the modelusing both plasticine and tape to ensure that the tube was positioned as flat as possibleon the surface of the model as shown in Figure 9 Preston-tube measurement were takenon the upper surface of the submarine model along a line directly above the centre-lineof the model For the dT = 02 and 05 mm wires and the grit case measurements weretaken from x = 73 mm to x = 1065 mm for a total of 18 stations For the dT = 01 mmwire measurements were limited to 3 stations between x = 305 mm and x = 442 mmThe stream-wise coordinates for the Preston tube measurements are given in the Table 2Data were acquired for a range of free-stream velocities from 40 to 70 ms in incrementsof 5 ms

For each nominal velocity the corresponding model Reynolds number was calcu-lated assuming standard temperature and atmospheric pressure conditions 20C and101 325 Pa respectively For each given test the temperature and static pressure of theair within the test section were logged and the air density and viscosity were calculatedTo account for daily variations in temperature and atmospheric pressure the freestream

12 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Flow direction

Figure 9 Preston tube located on the centre-line of the upper-surface of submarine

velocity was adjusted to ensure that the model Reynolds number remained constant foreach given nominal velocity condition as shown in Table 3

Table 2 Skin-friction measurement stations Where applicable the corresponding staticport number is given For the dT = 01 mm wire measurements were only taken at stations3050 3600 as well as an additional station at x = 4425 mm

xmm 731 787 843 900 1125 1350 1575 1800 2150Static port - - - 6 - 7 - 8 -

xmm 2500 3050 3600 5250 7000 8700 9500 10100 10650Static port 9 - 12 13 14 17 18 21 24

Table 3 Reynolds numbers (based on submarine length 135 m) corresponding to thenominal free-stream velocities

Nominal Uinfin 40 45 50 55 60 65 70 msRe 358 403 448 493 537 582 627 times106

37 Data Reduction

The static pressure readings from the pressure ports were converted to pressure coefficientsusing the relationship

Cp =ps minus pinfinpt minus pinfin

(11)

where pinfin is the reference free-stream static pressure pt is the reference free-stream totalpressure and ps is the static pressure on the surface of the submarine model

As explained in Section 34 all Preston tube pressures are measured relative to the free-stream static pressure In order to apply the Preston tube calibration (4)-(6) the loggedPreston-tube pressure differences (ie pp minus pinfin) must first be converted to a ∆p = pp minus ps

UNCLASSIFIED 13

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 13: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

1 Introduction

This work aims to understand flow fields about a submarine As part of this programa series of experiments have been conducted in the Low-Speed Wind Tunnel (LSWT) atthe Defence Science and Technology Organisation (DSTO) to quantify the skin-frictiondistributions on a generic submarine model and in the process investigate the effectivenessof a limited range of tripping devices The results also provide a reference data set forcomputational fluid dynamics (CFD) validation of a submarine model

When conducting tests in wind tunnels on a sub-scale model for results of the exper-iment to be transferable to the full-scale vehicle the flow patterns and load coefficientson the model and the full-size vehicle need to be made similar Ideally this is achievedthrough matching the Reynolds number of the flow over the model to that of the full-scalevehicle However in practice this is difficult to achieve and is not always possible To en-sure that the flow features on the model are representative of those for the full-size vehiclea tripping device can be used such that the boundary layers (ie regions of laminar flowlaminar-to-turbulent transition and turbulent flow) are made similar However differenttripping devices can impart different disturbances into the flow In order to correctly stim-ulate the boundary layer on the submarine model and avoid over- or under-stimulationthe type and size of tripping devices need to be selected for a given Reynolds numberor Reynolds number range and also for a specific trip location Additionally the chosentripping device will be specific to a given tunnel and would be dependent on factors suchas the level of free-stream turbulence in the tunnel

dT

Ud

Trip wire

xd

Laminar Transition Turbulent

Boundary-layeredge

U1

Figure 1 Diagrammatic representation of a boundary layer being tripped based on adiagram given by White (1974)

11 Boundary-Layer Transition

Boundary-layer transition is a complicated physical process dependent on instability mech-anisms including Tollmien-Schlichting waves crossflow and Gortler instabilities (see Reedamp Saric 2008) Over the years there have been numerous articles published on transi-tion both from experimental investigations and CFD analyses in low-speed transonic

UNCLASSIFIED 1

DSTOndashTRndash2898 UNCLASSIFIED

and hypersonic flow regimes (for example Schlatter amp Henningson 2009) Details of thetransition process are still not fully understood In the present report transition physicalprocesses are not considered instead attention is focused on how to stabilise the posi-tion of the transition using a tripping device and to ensure that the turbulent boundarylayer is neither under- or over-stimulated irrespective of the flow physics associated withtransition

12 Approach of Erm amp Joubert (1991)

A diagrammatic representation of a boundary layer being tripped is shown in Figure 1where dT is the height of the tripping device U1 is the streamwise velocity at the edge ofthe boundary layer xd is the location of the tripping device measured from the nose ofthe model and Ud is the velocity in the boundary layer at the top of the device

A question that had to be addressed was what is the best size and type of trippingdevice to use in the current experiments in the LSWT to trip the boundary layer on thesubmarine model Erm amp Joubert (1991) faced a similar question in their studies on low-Reynolds-number flows over a smooth flat surface in a zero pressure gradient For differenttypes of tripping devices they measured longitudinal skin-friction coefficients for a rangeof free-stream velocities Their data for a 12 mm wire tripping device are reproduced inFigure 2 From this figure it can be seen that as the velocity is increased from 8 ms thedevice imparts an increased amount of turbulent energy into the flow so that the laminar-to-turbulent transition region moves upstream They conjectured that correct stimulationis associated with a particular curve when the peaks of successive curves correspondingto higher velocities do not advance significantly upstream Velocities lower than thatcorresponding to the particular curve were obviously associated with under-stimulatedflows since the peaks of the curves were well downstream of the device and thus thedevice was therefore not completely effective in tripping the flow Since the velocitycorresponding to the particular curve establishes a turbulent boundary layer almost to thepossible upstream limit of turbulent flow it seemed reasonable to assume that the maineffect of higher velocities was to overstimulate the flow

The x-coordinate corresponding to the peaks of Figure 2 are plotted in Figure 3 as afunction of streamwise velocity and it is apparent that the above condition for correct stim-ulation was satisfied when the velocity was between 10 and 12 ms This corresponds to aminimum Reynolds number of the tripping device in the range of RedT = U1dT ν = 800to 960 where ν is the kinematic viscosity For the case where a trip device has aReynolds number greater than the minimum required the tripping device may overstim-ulate the flow Note over-stimulation does not necessarily result in higher skin-frictionwhen compared to a correctly stimulated layer Rather it means that the disturbanceintroduced by the tripping device is felt downstream of the transition region and leadsto a ldquonon-standardrdquo turbulent boundary initially developing Ideally to assess whetherover-stimulation has occurred complete velocity profiles in the turbulent region need tobe measured and compared against reference data sets such as those collated by Coles(1962)

It should be noted that in the current work the boundary layer develops in a pressuregradient with wall curvature in both the streamwise and spanwise directions Whereas

2 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

the work of Erm amp Joubert (1991) was undertaken on a flat plate zero pressure gradientthis means the RedT values given above cannot be applied directly to predict the trip sizerequired However the approach taken here broadly follows that of Erm amp Joubert (1991)in that a range of trip Reynolds numbers were tested (by varying both freestream velocityand trip size) and the skin-friction downstream of the trip measured

0 01 02x (m)

03 04 05

Figure 2 Cf vs x measurements for a 12 mm diameter trip wire for different free-streamvelocities as obtained by Erm amp Joubert (1991)

8 9 10 11 12 13 14

xlocation

(m)of

peakCf

Location of peak Cf

Location of trip device

01

02

0

Uinfin (ms)

Figure 3 Location of the peak Cf values shown in Figure 2

UNCLASSIFIED 3

DSTOndashTRndash2898 UNCLASSIFIED

13 Empirical Expressions to Determine Sizes of TrippingDevices

Researchers have proposed different empirical expressions for determining the size of deviceto use to trip the flow The relationships incorporate parameters including the height ofthe tripping device dT the velocity at the edge of the boundary layer U1 the velocity inthe undisturbed boundary layer at the top of the device Ud and the wall friction velocityevaluated at the device Uτ The friction velocity is defined by τ0 = ρU2

τ where τ0 is thesurface shear stress and ρ is the fluid density Recommendations for fully-effective trippingcover quite a wide range Tani et al (1940) proposed the criterion UτdT ν = 13 Fage ampPreston (1941) proposed UτdT ν = 20 Braslow amp Knox (1958) proposed UddT ν = 600and Gibbings (1959) proposed U1dT ν = 826 It should be noted that the criterion ofGibbings (1959) is based on a review of many data sets included those of Tani amp Sato(1956) and Fage amp Preston (1941) Gibbings (1959) expresses the Tani amp Sato (1956)and Fage amp Preston (1941) criteria as Reynolds numbers based on the freestream velocitywhich gives values of U1dT ν = 600 and 840 respectively The criterion given aboverepresent minimum values of the tripping device Reynolds number required to correctlytrip the boundary layer and agree with the results of Erm amp Joubert (1991)

An analysis of the literature for tests done on bodies of revolution indicated that thereis no consistent approach for selecting the size and type of device to use on such bodiesAppendix A gives details of devices used by different investigators for bodies of revolutiontogether with other experimental information Based on the freestream velocity and tripheight the Reynolds numbers of the trip devices given in Appendix A range from 200 to40 times 103 For the present investigation the approach used to establish the effects thatdifferent devices had on tripping laminar boundary layers was similar to that used byErm amp Joubert (1991) for a smooth flat plate in a zero pressure gradient Using theirtechnique it is possible to establish the size and type of tripping device to be used for agiven velocity to obtain correctly stimulated turbulent boundary layers

2 Preston-Tube Method of Measuring

Skin-Friction Coefficients

Skin-friction coefficients in a turbulent boundary layer flowing over a smooth surface canbe measured in a number of different ways (Fernholz et al 1996) including using Prestontubes (Preston 1954) from velocity profiles and using devices mounted flush with thesurface of a model Of the alternative approaches the Preston-tube method is convenientand is widely used The method makes use of a simple Pitot tube placed on the surfaceof a body and when used this way it is termed a Preston tube The method depends onan underlining assumption that in the region adjacent to the surface the flow is primarilydetermined by the surface shear stress and the properties of the fluid and is independentof factors such as pressure gradient and surface curvature The assumption implies thatthe velocity profile in a turbulent boundary layer adjacent to the surface is given by

U

Uτ= f

(Uτy

ν

)(1)

4 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

where U is the local stream-wise velocity Uτ is the friction velocity f is a universalfunction y is the wall normal coordinate and ν is the kinematic viscosity Equation (1) isoften referred to as the ldquolaw of the wallrdquo (Coles 1956)

A Pitot tube placed on the wall will measure a pressure relative to the wall staticpressure of ∆p = ρU22 at an effective coordinate y = c0d where d is the outer diameterof the Pitot tube and c0 is an unknown constant Substituting the values U =

radic(2∆pρ)

and y = cod into (1) yields a relationship between the wall shear stress fluid propertiesPreston-tube pressure difference and the tube diameter which is given by

2∆p

ρUτ2 =

[f

(Uτ c0d

ν

)]2 (2)

Alternatively for the purpose of measuring skin friction (2) can be expressed more con-veniently in the form

τ0d2

4ρν2= F

(∆pd2

4ρν2

)(3)

where c0 has been absorbed into the function F The function F represents the ldquocalibra-tionrdquo function for a Preston tube and several experimentally derived forms exist in theliterature (see Preston 1954 Patel 1965 Zagarola et al 2001) Generally the calibrationis determined by placing the Preston tube in a pipe flow where the wall shear stress (orfriction factor) can be determined accurately by measuring the pressure gradient in thepipe

For the data presented in this report the calibration of Patel (1965) was used todetermine the wall shear stress The calibration curve of Patel (1965) is given as follows

xlowast =ylowast + 2 log10(195ylowast + 410) for 55 ltUτd

2νlt 800 (4)

ylowast =08287 minus 01381xlowast + 01437xlowast2 minus 0006xlowast3 for 56 ltUτd

2νlt 55 and (5)

ylowast =1

2xlowast + 0037 for

Uτd

2νlt 56 (6)

where

xlowast = log10

(∆pd2

4ρν2

)and ylowast = log10

(τ0d

2

4ρν2

)

The local skin friction coefficient Cf is then found using

Cf =τ0

12ρU

21

(7)

where U1 is the streamwise velocity at the edge of the boundary layer

The calibration given by (4)-(6) is valid only for a hydrodynamically smooth surfaceA surface is considered hydrodynamically smooth provided that the height of surfaceroughness elements remain less than 5νUτ (Jimenez 2004) The minimum value of 5νUτthat was measured was approximately 4microm and the measured surface finish was found tobe an order of magnitude less than this value (Section 32) Hence the requirement of ahydrodynamically smooth surface is satisfied for this experiment

UNCLASSIFIED 5

DSTOndashTRndash2898 UNCLASSIFIED

The fundamental requirement for using a Preston tube is that the boundary layer isin a turbulent state and that the dimension of the Preston tube is such that it remainswithin the region where (1) is valid (ie from (4) Uτdν lt 1600) The diameter of thePreston tube for all experiments was d = 06 mm and this ensured that Uτdν remainedless than 1600 well within the range of the calibration (4)

It is known that for sufficiently strong pressure gradients the form of (1) changes (seeNickels 2004) Patel (1965) quantifies the effect of pressure gradients using the non-dimensional pressure gradient parameter1

p+x =ν

ρU3τ

dp

dx (8)

The error associated with using a Preston tube in pressure gradients is quantified by Patel(1965) and is given by the following inequalities

1 Adverse pressure gradient

Max Error 3 0 lt p+x lt 001 andUτd

νle 200 (9a)

Max Error 6 0 lt p+x lt 0015 andUτd

νle 250 (9b)

2 Favourable pressure gradient

Max Error 3 minus0005 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10a)

Max Error 6 minus0007 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10b)

The pressure gradient data are presented in Section 44 and were found to fall within thelimits of (9a) and (10a) indicating that the skin-friction coefficients are valid to withinplusmn3 This accuracy is similar to the alternative direct skin-friction measuring techniqueswhich typically achieve an accuracy of plusmn4 (Fernholz et al 1996)

The effect of model spanwise curvature on (4)-(6) is not quantified A reasonableassumption is that since the boundary layer thickness is much less than the model diameterthe effect of spanwise model curvature can be neglected

The Preston-tube method as outlined above requires that the boundary layer is in aturbulent state For this reason the method cannot be used to infer the skin friction atlocations were the boundary layer is in a laminar state However the ∆p values read by thePreston tube can be used to determine where laminar-to-turbulent transition occurs Theregion of transition is associated with a discontinuity in ∆p when plotted as a functionof streamwise coordinate x as shown by Erm amp Joubert (1991)

1for clarity we have adopted the notation for the pressure gradient parameter used by Nickels (2004)Patel (1965) uses the symbol ∆

6 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 4 LSWT Layout see Erm (2003)

3 Test Program

In this preliminary investigation four different tripping devices were used to investigatethe effect of the device on the skin-friction profile of a generic sub-scale submarine modelTests were conducted both with and without the tripping devices at a range of nominalfree-stream velocities Uinfin ranging from Uinfin = 40 to 70 ms to assess their effectivenessin tripping the boundary layer

31 Test Facility

The Low-Speed Wind Tunnel at DSTO is a closed circuit continuous flow tunnel with acontraction ratio of 41 The test section has an irregular octagonal shape with a heightof 213 m a width of 274 m and a length of 6553 m with a longitudinal turbulenceintensity of approximately 04 in the region where the models are tested (see Erm2003) An outline of the plan of the wind tunnel is shown in Figure 4 Free-streamvelocities were measured using static pressure rings at the upstream and downstreamends of the contraction A Pitot-static probe mounted on the side wall near the front ofthe working section was used to provide an independent measurement of the free-streamvelocity

32 Test Model

The sub-scale submarine model utilised in these tests is referred to as the Joubert modelsince the geometry is based on the work of Joubert (2004) and Joubert (2006) as well asLoid amp Bystrom (1983) The model was designed for the purpose of experimental and

UNCLASSIFIED 7

DSTOndashTRndash2898 UNCLASSIFIED

1

2 345

6 7 8 91011

12 13 141516

17 181920

212223

24 252627

28 29 303132

33 34

35

Top view

Side view

Figure 5 Schematic of scale model showing static-pressure port locations green and redmarkers represent the starboard and port static-pressure ports respectively

numerical studies and has no full-scale equivalent While the full model includes a casingcentre fin and control surfaces all tests reported here were conducted on the axisymmetricbody shape only

The model was machined from aluminum and consists of an ellipsoidal nose a cylin-drical centre-body and a streamlined tail section At the design stage an N6 surface finishwas specified for the model which corresponds to a roughness of 08microm in waviness Af-ter manufacture the surface finish was checked using a Surface Roughness Indicator andthe finish was found to be better than the design specification The model was anodisedwhich increased the thickness of the natural oxide layer by about 10microm

The model is 1350 mm long with a maximum diameter of 185 mm and slendernessratio of 73 where the slenderness ratio is defined as hull length divided by maximumhull diameter The model contains 21 longitudinal static-pressure ports on the centre-lineof the upper surface and 14 lateral static-pressure ports offset to the port and starboardsides of the upper surface centre-line Figure 5 shows the stream-wise location of thestatic-pressure ports

The model was supported by a single pylon as shown in Figure 6 All tests were carriedout at zero angle of yaw and zero angle of pitch The origin of the body coordinate systemis located at the nose of the submarine model The x-axis corresponds to the axis ofsymmetry of the model

8 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 6 Submarine model mounted in LSWT showing pylon support and pitch controlarm

UNCLASSIFIED 9

DSTOndashTRndash2898 UNCLASSIFIED

Table 1 Details of tripping devices where the Reynolds number is based on the height ofthe device The minimum Reynolds number and maximum Reynolds number correspondto nominal freestream velocities of Uinfin = 40 ms and Uinfin = 70 ms respectively where his the height of the grit and w is the width of the grit

Device Dimensions (mm) RedT (min) RedT (max)

Wire 1 dT = 01 281 496Wire 2 dT = 02 577 1015Wire 3 dT = 05 1443 256680 Grit h = 021 w = 3 605 1073

33 Tripping Devices

In this work four tripping devices were tested and consisted of circular wires with diame-ters dT = 01 02 and 05 mm as well as a distributed silicon carbide grit of size 80 havinga width of 3 mm The circular wires were bent to conform to the local diameter of thesubmarine and then attached with ldquosuper-gluerdquo such that there was no gap between thewire and the model surface Figure 7 The silicon carbide grit is prepared by distributinga layer of grit on double-sided sticky tape the tape is then adhered to the submarineFigure 8 The tripping devices were attached to the submarine model circumferentiallylocated at a streamwise coordinate of x = 675 mm measured from the nose of the sub-marine which corresponds to 5 of the total model length The dimensions of the tripdevices along with the Reynolds number range of the trip devices are summarised inTable 1 Note that the Reynolds number of the trip device is defined as RedT = U1dT νwhere for the case of the 80 grit dT is replaced by the grit height h

34 Pressure Scanners

Pressure Systems Incorporated (PSI) brand pressure scanners were used to measure allstatic and total pressures The pressure scanners are differential pressure measurementunits consisting of an array of silicon piezoresistive pressure sensors one for each pressureport The outputs of the sensors are electronically multiplexed through a single on-boardinstrumentation amplifier using binary addressing The scanners include a two-positioncalibration manifold actuated by momentary pulses of control pressures In the calibrateposition all sensors are connected to a common calibration pressure port A series ofaccurately-measured pressures is applied through this port to characterize the sensorsProper and periodic on-line calibration maintains static errors within plusmn003 or betterof the full-scale pressure range

The pressure scanners are controlled and sampled using a PSI 8400 electronic measure-ment system It is a modular parallel processing system for high-speed pressure scanningat up to 20000 measurements per second and allows the use of digitally temperaturecompensated pressure scanners

Two differential pressure scanners were used in the experiments All pressures aremeasured relative to the free-stream static pressure pinfin as measured by the referencefree-stream Pitot-static probe Each pressure scanner contained 32 ports The full-scale

10 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 7 Location of trip wire

Figure 8 Photo showing the 3 mm wide band of 80 grit transition strip

UNCLASSIFIED 11

DSTOndashTRndash2898 UNCLASSIFIED

pressure range of the scanners is 249 kPa (ldquo10 inches-of-water scannerrdquo) and 689 kPa(ldquo1 psi scannerrdquo) The 689 kPa scanner was used to read the static pressure at the longi-tudinal ports as well as the output from the Preston tube and the Pitot-static probe

For the purpose of cross-checking and for redundancy the Preston tube was connectedto two independent ports of the 689 kPa scanner and the two readings averaged For thisscanner pressures could be read to an accuracy of 6890 times 00003 Pa ie about 2 Pa Theminimum ∆p measured by the Preston tube was 145 Pa which gives a pressure scannerresolution of 14 However this minimum ∆p was recorded for a location where thePreston tube was in a laminar boundary layer and such data is only useful in a qualitativesense (see Section 2) For locations were the boundary layer is turbulent the minimum ∆pwas 340 Pa which gives a pressure scanner resolution of 06 The 249 kPa scanner wasused mainly to acquire the static pressures at the lateral ports

35 Data Acquisition Software

A software package called ImPressOne was used which communicates with the PSI 8400and displays and acquires the pressure data for the model under test For the staticpressure measurements 100 readings were acquired at each pressure port at a samplingrate of 20 Hz For the Preston-tube measurements the sample rate was increased and100 samples were acquired at each pressure port at a sampling rate of 50 Hz for eachfree-stream velocity

36 Experimental Procedure

The hull was tested with each of the selected tripping devices listed in Table 1 as wellas without a tripping device resulting in five different test configurations For each testconfiguration the static pressures were initially acquired for that particular configurationfollowed by the Preston-tube measurements

A Preston tube having a diameter of 06 mm was attached to the surface of the modelusing both plasticine and tape to ensure that the tube was positioned as flat as possibleon the surface of the model as shown in Figure 9 Preston-tube measurement were takenon the upper surface of the submarine model along a line directly above the centre-lineof the model For the dT = 02 and 05 mm wires and the grit case measurements weretaken from x = 73 mm to x = 1065 mm for a total of 18 stations For the dT = 01 mmwire measurements were limited to 3 stations between x = 305 mm and x = 442 mmThe stream-wise coordinates for the Preston tube measurements are given in the Table 2Data were acquired for a range of free-stream velocities from 40 to 70 ms in incrementsof 5 ms

For each nominal velocity the corresponding model Reynolds number was calcu-lated assuming standard temperature and atmospheric pressure conditions 20C and101 325 Pa respectively For each given test the temperature and static pressure of theair within the test section were logged and the air density and viscosity were calculatedTo account for daily variations in temperature and atmospheric pressure the freestream

12 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Flow direction

Figure 9 Preston tube located on the centre-line of the upper-surface of submarine

velocity was adjusted to ensure that the model Reynolds number remained constant foreach given nominal velocity condition as shown in Table 3

Table 2 Skin-friction measurement stations Where applicable the corresponding staticport number is given For the dT = 01 mm wire measurements were only taken at stations3050 3600 as well as an additional station at x = 4425 mm

xmm 731 787 843 900 1125 1350 1575 1800 2150Static port - - - 6 - 7 - 8 -

xmm 2500 3050 3600 5250 7000 8700 9500 10100 10650Static port 9 - 12 13 14 17 18 21 24

Table 3 Reynolds numbers (based on submarine length 135 m) corresponding to thenominal free-stream velocities

Nominal Uinfin 40 45 50 55 60 65 70 msRe 358 403 448 493 537 582 627 times106

37 Data Reduction

The static pressure readings from the pressure ports were converted to pressure coefficientsusing the relationship

Cp =ps minus pinfinpt minus pinfin

(11)

where pinfin is the reference free-stream static pressure pt is the reference free-stream totalpressure and ps is the static pressure on the surface of the submarine model

As explained in Section 34 all Preston tube pressures are measured relative to the free-stream static pressure In order to apply the Preston tube calibration (4)-(6) the loggedPreston-tube pressure differences (ie pp minus pinfin) must first be converted to a ∆p = pp minus ps

UNCLASSIFIED 13

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 14: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

and hypersonic flow regimes (for example Schlatter amp Henningson 2009) Details of thetransition process are still not fully understood In the present report transition physicalprocesses are not considered instead attention is focused on how to stabilise the posi-tion of the transition using a tripping device and to ensure that the turbulent boundarylayer is neither under- or over-stimulated irrespective of the flow physics associated withtransition

12 Approach of Erm amp Joubert (1991)

A diagrammatic representation of a boundary layer being tripped is shown in Figure 1where dT is the height of the tripping device U1 is the streamwise velocity at the edge ofthe boundary layer xd is the location of the tripping device measured from the nose ofthe model and Ud is the velocity in the boundary layer at the top of the device

A question that had to be addressed was what is the best size and type of trippingdevice to use in the current experiments in the LSWT to trip the boundary layer on thesubmarine model Erm amp Joubert (1991) faced a similar question in their studies on low-Reynolds-number flows over a smooth flat surface in a zero pressure gradient For differenttypes of tripping devices they measured longitudinal skin-friction coefficients for a rangeof free-stream velocities Their data for a 12 mm wire tripping device are reproduced inFigure 2 From this figure it can be seen that as the velocity is increased from 8 ms thedevice imparts an increased amount of turbulent energy into the flow so that the laminar-to-turbulent transition region moves upstream They conjectured that correct stimulationis associated with a particular curve when the peaks of successive curves correspondingto higher velocities do not advance significantly upstream Velocities lower than thatcorresponding to the particular curve were obviously associated with under-stimulatedflows since the peaks of the curves were well downstream of the device and thus thedevice was therefore not completely effective in tripping the flow Since the velocitycorresponding to the particular curve establishes a turbulent boundary layer almost to thepossible upstream limit of turbulent flow it seemed reasonable to assume that the maineffect of higher velocities was to overstimulate the flow

The x-coordinate corresponding to the peaks of Figure 2 are plotted in Figure 3 as afunction of streamwise velocity and it is apparent that the above condition for correct stim-ulation was satisfied when the velocity was between 10 and 12 ms This corresponds to aminimum Reynolds number of the tripping device in the range of RedT = U1dT ν = 800to 960 where ν is the kinematic viscosity For the case where a trip device has aReynolds number greater than the minimum required the tripping device may overstim-ulate the flow Note over-stimulation does not necessarily result in higher skin-frictionwhen compared to a correctly stimulated layer Rather it means that the disturbanceintroduced by the tripping device is felt downstream of the transition region and leadsto a ldquonon-standardrdquo turbulent boundary initially developing Ideally to assess whetherover-stimulation has occurred complete velocity profiles in the turbulent region need tobe measured and compared against reference data sets such as those collated by Coles(1962)

It should be noted that in the current work the boundary layer develops in a pressuregradient with wall curvature in both the streamwise and spanwise directions Whereas

2 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

the work of Erm amp Joubert (1991) was undertaken on a flat plate zero pressure gradientthis means the RedT values given above cannot be applied directly to predict the trip sizerequired However the approach taken here broadly follows that of Erm amp Joubert (1991)in that a range of trip Reynolds numbers were tested (by varying both freestream velocityand trip size) and the skin-friction downstream of the trip measured

0 01 02x (m)

03 04 05

Figure 2 Cf vs x measurements for a 12 mm diameter trip wire for different free-streamvelocities as obtained by Erm amp Joubert (1991)

8 9 10 11 12 13 14

xlocation

(m)of

peakCf

Location of peak Cf

Location of trip device

01

02

0

Uinfin (ms)

Figure 3 Location of the peak Cf values shown in Figure 2

UNCLASSIFIED 3

DSTOndashTRndash2898 UNCLASSIFIED

13 Empirical Expressions to Determine Sizes of TrippingDevices

Researchers have proposed different empirical expressions for determining the size of deviceto use to trip the flow The relationships incorporate parameters including the height ofthe tripping device dT the velocity at the edge of the boundary layer U1 the velocity inthe undisturbed boundary layer at the top of the device Ud and the wall friction velocityevaluated at the device Uτ The friction velocity is defined by τ0 = ρU2

τ where τ0 is thesurface shear stress and ρ is the fluid density Recommendations for fully-effective trippingcover quite a wide range Tani et al (1940) proposed the criterion UτdT ν = 13 Fage ampPreston (1941) proposed UτdT ν = 20 Braslow amp Knox (1958) proposed UddT ν = 600and Gibbings (1959) proposed U1dT ν = 826 It should be noted that the criterion ofGibbings (1959) is based on a review of many data sets included those of Tani amp Sato(1956) and Fage amp Preston (1941) Gibbings (1959) expresses the Tani amp Sato (1956)and Fage amp Preston (1941) criteria as Reynolds numbers based on the freestream velocitywhich gives values of U1dT ν = 600 and 840 respectively The criterion given aboverepresent minimum values of the tripping device Reynolds number required to correctlytrip the boundary layer and agree with the results of Erm amp Joubert (1991)

An analysis of the literature for tests done on bodies of revolution indicated that thereis no consistent approach for selecting the size and type of device to use on such bodiesAppendix A gives details of devices used by different investigators for bodies of revolutiontogether with other experimental information Based on the freestream velocity and tripheight the Reynolds numbers of the trip devices given in Appendix A range from 200 to40 times 103 For the present investigation the approach used to establish the effects thatdifferent devices had on tripping laminar boundary layers was similar to that used byErm amp Joubert (1991) for a smooth flat plate in a zero pressure gradient Using theirtechnique it is possible to establish the size and type of tripping device to be used for agiven velocity to obtain correctly stimulated turbulent boundary layers

2 Preston-Tube Method of Measuring

Skin-Friction Coefficients

Skin-friction coefficients in a turbulent boundary layer flowing over a smooth surface canbe measured in a number of different ways (Fernholz et al 1996) including using Prestontubes (Preston 1954) from velocity profiles and using devices mounted flush with thesurface of a model Of the alternative approaches the Preston-tube method is convenientand is widely used The method makes use of a simple Pitot tube placed on the surfaceof a body and when used this way it is termed a Preston tube The method depends onan underlining assumption that in the region adjacent to the surface the flow is primarilydetermined by the surface shear stress and the properties of the fluid and is independentof factors such as pressure gradient and surface curvature The assumption implies thatthe velocity profile in a turbulent boundary layer adjacent to the surface is given by

U

Uτ= f

(Uτy

ν

)(1)

4 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

where U is the local stream-wise velocity Uτ is the friction velocity f is a universalfunction y is the wall normal coordinate and ν is the kinematic viscosity Equation (1) isoften referred to as the ldquolaw of the wallrdquo (Coles 1956)

A Pitot tube placed on the wall will measure a pressure relative to the wall staticpressure of ∆p = ρU22 at an effective coordinate y = c0d where d is the outer diameterof the Pitot tube and c0 is an unknown constant Substituting the values U =

radic(2∆pρ)

and y = cod into (1) yields a relationship between the wall shear stress fluid propertiesPreston-tube pressure difference and the tube diameter which is given by

2∆p

ρUτ2 =

[f

(Uτ c0d

ν

)]2 (2)

Alternatively for the purpose of measuring skin friction (2) can be expressed more con-veniently in the form

τ0d2

4ρν2= F

(∆pd2

4ρν2

)(3)

where c0 has been absorbed into the function F The function F represents the ldquocalibra-tionrdquo function for a Preston tube and several experimentally derived forms exist in theliterature (see Preston 1954 Patel 1965 Zagarola et al 2001) Generally the calibrationis determined by placing the Preston tube in a pipe flow where the wall shear stress (orfriction factor) can be determined accurately by measuring the pressure gradient in thepipe

For the data presented in this report the calibration of Patel (1965) was used todetermine the wall shear stress The calibration curve of Patel (1965) is given as follows

xlowast =ylowast + 2 log10(195ylowast + 410) for 55 ltUτd

2νlt 800 (4)

ylowast =08287 minus 01381xlowast + 01437xlowast2 minus 0006xlowast3 for 56 ltUτd

2νlt 55 and (5)

ylowast =1

2xlowast + 0037 for

Uτd

2νlt 56 (6)

where

xlowast = log10

(∆pd2

4ρν2

)and ylowast = log10

(τ0d

2

4ρν2

)

The local skin friction coefficient Cf is then found using

Cf =τ0

12ρU

21

(7)

where U1 is the streamwise velocity at the edge of the boundary layer

The calibration given by (4)-(6) is valid only for a hydrodynamically smooth surfaceA surface is considered hydrodynamically smooth provided that the height of surfaceroughness elements remain less than 5νUτ (Jimenez 2004) The minimum value of 5νUτthat was measured was approximately 4microm and the measured surface finish was found tobe an order of magnitude less than this value (Section 32) Hence the requirement of ahydrodynamically smooth surface is satisfied for this experiment

UNCLASSIFIED 5

DSTOndashTRndash2898 UNCLASSIFIED

The fundamental requirement for using a Preston tube is that the boundary layer isin a turbulent state and that the dimension of the Preston tube is such that it remainswithin the region where (1) is valid (ie from (4) Uτdν lt 1600) The diameter of thePreston tube for all experiments was d = 06 mm and this ensured that Uτdν remainedless than 1600 well within the range of the calibration (4)

It is known that for sufficiently strong pressure gradients the form of (1) changes (seeNickels 2004) Patel (1965) quantifies the effect of pressure gradients using the non-dimensional pressure gradient parameter1

p+x =ν

ρU3τ

dp

dx (8)

The error associated with using a Preston tube in pressure gradients is quantified by Patel(1965) and is given by the following inequalities

1 Adverse pressure gradient

Max Error 3 0 lt p+x lt 001 andUτd

νle 200 (9a)

Max Error 6 0 lt p+x lt 0015 andUτd

νle 250 (9b)

2 Favourable pressure gradient

Max Error 3 minus0005 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10a)

Max Error 6 minus0007 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10b)

The pressure gradient data are presented in Section 44 and were found to fall within thelimits of (9a) and (10a) indicating that the skin-friction coefficients are valid to withinplusmn3 This accuracy is similar to the alternative direct skin-friction measuring techniqueswhich typically achieve an accuracy of plusmn4 (Fernholz et al 1996)

The effect of model spanwise curvature on (4)-(6) is not quantified A reasonableassumption is that since the boundary layer thickness is much less than the model diameterthe effect of spanwise model curvature can be neglected

The Preston-tube method as outlined above requires that the boundary layer is in aturbulent state For this reason the method cannot be used to infer the skin friction atlocations were the boundary layer is in a laminar state However the ∆p values read by thePreston tube can be used to determine where laminar-to-turbulent transition occurs Theregion of transition is associated with a discontinuity in ∆p when plotted as a functionof streamwise coordinate x as shown by Erm amp Joubert (1991)

1for clarity we have adopted the notation for the pressure gradient parameter used by Nickels (2004)Patel (1965) uses the symbol ∆

6 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 4 LSWT Layout see Erm (2003)

3 Test Program

In this preliminary investigation four different tripping devices were used to investigatethe effect of the device on the skin-friction profile of a generic sub-scale submarine modelTests were conducted both with and without the tripping devices at a range of nominalfree-stream velocities Uinfin ranging from Uinfin = 40 to 70 ms to assess their effectivenessin tripping the boundary layer

31 Test Facility

The Low-Speed Wind Tunnel at DSTO is a closed circuit continuous flow tunnel with acontraction ratio of 41 The test section has an irregular octagonal shape with a heightof 213 m a width of 274 m and a length of 6553 m with a longitudinal turbulenceintensity of approximately 04 in the region where the models are tested (see Erm2003) An outline of the plan of the wind tunnel is shown in Figure 4 Free-streamvelocities were measured using static pressure rings at the upstream and downstreamends of the contraction A Pitot-static probe mounted on the side wall near the front ofthe working section was used to provide an independent measurement of the free-streamvelocity

32 Test Model

The sub-scale submarine model utilised in these tests is referred to as the Joubert modelsince the geometry is based on the work of Joubert (2004) and Joubert (2006) as well asLoid amp Bystrom (1983) The model was designed for the purpose of experimental and

UNCLASSIFIED 7

DSTOndashTRndash2898 UNCLASSIFIED

1

2 345

6 7 8 91011

12 13 141516

17 181920

212223

24 252627

28 29 303132

33 34

35

Top view

Side view

Figure 5 Schematic of scale model showing static-pressure port locations green and redmarkers represent the starboard and port static-pressure ports respectively

numerical studies and has no full-scale equivalent While the full model includes a casingcentre fin and control surfaces all tests reported here were conducted on the axisymmetricbody shape only

The model was machined from aluminum and consists of an ellipsoidal nose a cylin-drical centre-body and a streamlined tail section At the design stage an N6 surface finishwas specified for the model which corresponds to a roughness of 08microm in waviness Af-ter manufacture the surface finish was checked using a Surface Roughness Indicator andthe finish was found to be better than the design specification The model was anodisedwhich increased the thickness of the natural oxide layer by about 10microm

The model is 1350 mm long with a maximum diameter of 185 mm and slendernessratio of 73 where the slenderness ratio is defined as hull length divided by maximumhull diameter The model contains 21 longitudinal static-pressure ports on the centre-lineof the upper surface and 14 lateral static-pressure ports offset to the port and starboardsides of the upper surface centre-line Figure 5 shows the stream-wise location of thestatic-pressure ports

The model was supported by a single pylon as shown in Figure 6 All tests were carriedout at zero angle of yaw and zero angle of pitch The origin of the body coordinate systemis located at the nose of the submarine model The x-axis corresponds to the axis ofsymmetry of the model

8 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 6 Submarine model mounted in LSWT showing pylon support and pitch controlarm

UNCLASSIFIED 9

DSTOndashTRndash2898 UNCLASSIFIED

Table 1 Details of tripping devices where the Reynolds number is based on the height ofthe device The minimum Reynolds number and maximum Reynolds number correspondto nominal freestream velocities of Uinfin = 40 ms and Uinfin = 70 ms respectively where his the height of the grit and w is the width of the grit

Device Dimensions (mm) RedT (min) RedT (max)

Wire 1 dT = 01 281 496Wire 2 dT = 02 577 1015Wire 3 dT = 05 1443 256680 Grit h = 021 w = 3 605 1073

33 Tripping Devices

In this work four tripping devices were tested and consisted of circular wires with diame-ters dT = 01 02 and 05 mm as well as a distributed silicon carbide grit of size 80 havinga width of 3 mm The circular wires were bent to conform to the local diameter of thesubmarine and then attached with ldquosuper-gluerdquo such that there was no gap between thewire and the model surface Figure 7 The silicon carbide grit is prepared by distributinga layer of grit on double-sided sticky tape the tape is then adhered to the submarineFigure 8 The tripping devices were attached to the submarine model circumferentiallylocated at a streamwise coordinate of x = 675 mm measured from the nose of the sub-marine which corresponds to 5 of the total model length The dimensions of the tripdevices along with the Reynolds number range of the trip devices are summarised inTable 1 Note that the Reynolds number of the trip device is defined as RedT = U1dT νwhere for the case of the 80 grit dT is replaced by the grit height h

34 Pressure Scanners

Pressure Systems Incorporated (PSI) brand pressure scanners were used to measure allstatic and total pressures The pressure scanners are differential pressure measurementunits consisting of an array of silicon piezoresistive pressure sensors one for each pressureport The outputs of the sensors are electronically multiplexed through a single on-boardinstrumentation amplifier using binary addressing The scanners include a two-positioncalibration manifold actuated by momentary pulses of control pressures In the calibrateposition all sensors are connected to a common calibration pressure port A series ofaccurately-measured pressures is applied through this port to characterize the sensorsProper and periodic on-line calibration maintains static errors within plusmn003 or betterof the full-scale pressure range

The pressure scanners are controlled and sampled using a PSI 8400 electronic measure-ment system It is a modular parallel processing system for high-speed pressure scanningat up to 20000 measurements per second and allows the use of digitally temperaturecompensated pressure scanners

Two differential pressure scanners were used in the experiments All pressures aremeasured relative to the free-stream static pressure pinfin as measured by the referencefree-stream Pitot-static probe Each pressure scanner contained 32 ports The full-scale

10 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 7 Location of trip wire

Figure 8 Photo showing the 3 mm wide band of 80 grit transition strip

UNCLASSIFIED 11

DSTOndashTRndash2898 UNCLASSIFIED

pressure range of the scanners is 249 kPa (ldquo10 inches-of-water scannerrdquo) and 689 kPa(ldquo1 psi scannerrdquo) The 689 kPa scanner was used to read the static pressure at the longi-tudinal ports as well as the output from the Preston tube and the Pitot-static probe

For the purpose of cross-checking and for redundancy the Preston tube was connectedto two independent ports of the 689 kPa scanner and the two readings averaged For thisscanner pressures could be read to an accuracy of 6890 times 00003 Pa ie about 2 Pa Theminimum ∆p measured by the Preston tube was 145 Pa which gives a pressure scannerresolution of 14 However this minimum ∆p was recorded for a location where thePreston tube was in a laminar boundary layer and such data is only useful in a qualitativesense (see Section 2) For locations were the boundary layer is turbulent the minimum ∆pwas 340 Pa which gives a pressure scanner resolution of 06 The 249 kPa scanner wasused mainly to acquire the static pressures at the lateral ports

35 Data Acquisition Software

A software package called ImPressOne was used which communicates with the PSI 8400and displays and acquires the pressure data for the model under test For the staticpressure measurements 100 readings were acquired at each pressure port at a samplingrate of 20 Hz For the Preston-tube measurements the sample rate was increased and100 samples were acquired at each pressure port at a sampling rate of 50 Hz for eachfree-stream velocity

36 Experimental Procedure

The hull was tested with each of the selected tripping devices listed in Table 1 as wellas without a tripping device resulting in five different test configurations For each testconfiguration the static pressures were initially acquired for that particular configurationfollowed by the Preston-tube measurements

A Preston tube having a diameter of 06 mm was attached to the surface of the modelusing both plasticine and tape to ensure that the tube was positioned as flat as possibleon the surface of the model as shown in Figure 9 Preston-tube measurement were takenon the upper surface of the submarine model along a line directly above the centre-lineof the model For the dT = 02 and 05 mm wires and the grit case measurements weretaken from x = 73 mm to x = 1065 mm for a total of 18 stations For the dT = 01 mmwire measurements were limited to 3 stations between x = 305 mm and x = 442 mmThe stream-wise coordinates for the Preston tube measurements are given in the Table 2Data were acquired for a range of free-stream velocities from 40 to 70 ms in incrementsof 5 ms

For each nominal velocity the corresponding model Reynolds number was calcu-lated assuming standard temperature and atmospheric pressure conditions 20C and101 325 Pa respectively For each given test the temperature and static pressure of theair within the test section were logged and the air density and viscosity were calculatedTo account for daily variations in temperature and atmospheric pressure the freestream

12 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Flow direction

Figure 9 Preston tube located on the centre-line of the upper-surface of submarine

velocity was adjusted to ensure that the model Reynolds number remained constant foreach given nominal velocity condition as shown in Table 3

Table 2 Skin-friction measurement stations Where applicable the corresponding staticport number is given For the dT = 01 mm wire measurements were only taken at stations3050 3600 as well as an additional station at x = 4425 mm

xmm 731 787 843 900 1125 1350 1575 1800 2150Static port - - - 6 - 7 - 8 -

xmm 2500 3050 3600 5250 7000 8700 9500 10100 10650Static port 9 - 12 13 14 17 18 21 24

Table 3 Reynolds numbers (based on submarine length 135 m) corresponding to thenominal free-stream velocities

Nominal Uinfin 40 45 50 55 60 65 70 msRe 358 403 448 493 537 582 627 times106

37 Data Reduction

The static pressure readings from the pressure ports were converted to pressure coefficientsusing the relationship

Cp =ps minus pinfinpt minus pinfin

(11)

where pinfin is the reference free-stream static pressure pt is the reference free-stream totalpressure and ps is the static pressure on the surface of the submarine model

As explained in Section 34 all Preston tube pressures are measured relative to the free-stream static pressure In order to apply the Preston tube calibration (4)-(6) the loggedPreston-tube pressure differences (ie pp minus pinfin) must first be converted to a ∆p = pp minus ps

UNCLASSIFIED 13

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 15: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

the work of Erm amp Joubert (1991) was undertaken on a flat plate zero pressure gradientthis means the RedT values given above cannot be applied directly to predict the trip sizerequired However the approach taken here broadly follows that of Erm amp Joubert (1991)in that a range of trip Reynolds numbers were tested (by varying both freestream velocityand trip size) and the skin-friction downstream of the trip measured

0 01 02x (m)

03 04 05

Figure 2 Cf vs x measurements for a 12 mm diameter trip wire for different free-streamvelocities as obtained by Erm amp Joubert (1991)

8 9 10 11 12 13 14

xlocation

(m)of

peakCf

Location of peak Cf

Location of trip device

01

02

0

Uinfin (ms)

Figure 3 Location of the peak Cf values shown in Figure 2

UNCLASSIFIED 3

DSTOndashTRndash2898 UNCLASSIFIED

13 Empirical Expressions to Determine Sizes of TrippingDevices

Researchers have proposed different empirical expressions for determining the size of deviceto use to trip the flow The relationships incorporate parameters including the height ofthe tripping device dT the velocity at the edge of the boundary layer U1 the velocity inthe undisturbed boundary layer at the top of the device Ud and the wall friction velocityevaluated at the device Uτ The friction velocity is defined by τ0 = ρU2

τ where τ0 is thesurface shear stress and ρ is the fluid density Recommendations for fully-effective trippingcover quite a wide range Tani et al (1940) proposed the criterion UτdT ν = 13 Fage ampPreston (1941) proposed UτdT ν = 20 Braslow amp Knox (1958) proposed UddT ν = 600and Gibbings (1959) proposed U1dT ν = 826 It should be noted that the criterion ofGibbings (1959) is based on a review of many data sets included those of Tani amp Sato(1956) and Fage amp Preston (1941) Gibbings (1959) expresses the Tani amp Sato (1956)and Fage amp Preston (1941) criteria as Reynolds numbers based on the freestream velocitywhich gives values of U1dT ν = 600 and 840 respectively The criterion given aboverepresent minimum values of the tripping device Reynolds number required to correctlytrip the boundary layer and agree with the results of Erm amp Joubert (1991)

An analysis of the literature for tests done on bodies of revolution indicated that thereis no consistent approach for selecting the size and type of device to use on such bodiesAppendix A gives details of devices used by different investigators for bodies of revolutiontogether with other experimental information Based on the freestream velocity and tripheight the Reynolds numbers of the trip devices given in Appendix A range from 200 to40 times 103 For the present investigation the approach used to establish the effects thatdifferent devices had on tripping laminar boundary layers was similar to that used byErm amp Joubert (1991) for a smooth flat plate in a zero pressure gradient Using theirtechnique it is possible to establish the size and type of tripping device to be used for agiven velocity to obtain correctly stimulated turbulent boundary layers

2 Preston-Tube Method of Measuring

Skin-Friction Coefficients

Skin-friction coefficients in a turbulent boundary layer flowing over a smooth surface canbe measured in a number of different ways (Fernholz et al 1996) including using Prestontubes (Preston 1954) from velocity profiles and using devices mounted flush with thesurface of a model Of the alternative approaches the Preston-tube method is convenientand is widely used The method makes use of a simple Pitot tube placed on the surfaceof a body and when used this way it is termed a Preston tube The method depends onan underlining assumption that in the region adjacent to the surface the flow is primarilydetermined by the surface shear stress and the properties of the fluid and is independentof factors such as pressure gradient and surface curvature The assumption implies thatthe velocity profile in a turbulent boundary layer adjacent to the surface is given by

U

Uτ= f

(Uτy

ν

)(1)

4 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

where U is the local stream-wise velocity Uτ is the friction velocity f is a universalfunction y is the wall normal coordinate and ν is the kinematic viscosity Equation (1) isoften referred to as the ldquolaw of the wallrdquo (Coles 1956)

A Pitot tube placed on the wall will measure a pressure relative to the wall staticpressure of ∆p = ρU22 at an effective coordinate y = c0d where d is the outer diameterof the Pitot tube and c0 is an unknown constant Substituting the values U =

radic(2∆pρ)

and y = cod into (1) yields a relationship between the wall shear stress fluid propertiesPreston-tube pressure difference and the tube diameter which is given by

2∆p

ρUτ2 =

[f

(Uτ c0d

ν

)]2 (2)

Alternatively for the purpose of measuring skin friction (2) can be expressed more con-veniently in the form

τ0d2

4ρν2= F

(∆pd2

4ρν2

)(3)

where c0 has been absorbed into the function F The function F represents the ldquocalibra-tionrdquo function for a Preston tube and several experimentally derived forms exist in theliterature (see Preston 1954 Patel 1965 Zagarola et al 2001) Generally the calibrationis determined by placing the Preston tube in a pipe flow where the wall shear stress (orfriction factor) can be determined accurately by measuring the pressure gradient in thepipe

For the data presented in this report the calibration of Patel (1965) was used todetermine the wall shear stress The calibration curve of Patel (1965) is given as follows

xlowast =ylowast + 2 log10(195ylowast + 410) for 55 ltUτd

2νlt 800 (4)

ylowast =08287 minus 01381xlowast + 01437xlowast2 minus 0006xlowast3 for 56 ltUτd

2νlt 55 and (5)

ylowast =1

2xlowast + 0037 for

Uτd

2νlt 56 (6)

where

xlowast = log10

(∆pd2

4ρν2

)and ylowast = log10

(τ0d

2

4ρν2

)

The local skin friction coefficient Cf is then found using

Cf =τ0

12ρU

21

(7)

where U1 is the streamwise velocity at the edge of the boundary layer

The calibration given by (4)-(6) is valid only for a hydrodynamically smooth surfaceA surface is considered hydrodynamically smooth provided that the height of surfaceroughness elements remain less than 5νUτ (Jimenez 2004) The minimum value of 5νUτthat was measured was approximately 4microm and the measured surface finish was found tobe an order of magnitude less than this value (Section 32) Hence the requirement of ahydrodynamically smooth surface is satisfied for this experiment

UNCLASSIFIED 5

DSTOndashTRndash2898 UNCLASSIFIED

The fundamental requirement for using a Preston tube is that the boundary layer isin a turbulent state and that the dimension of the Preston tube is such that it remainswithin the region where (1) is valid (ie from (4) Uτdν lt 1600) The diameter of thePreston tube for all experiments was d = 06 mm and this ensured that Uτdν remainedless than 1600 well within the range of the calibration (4)

It is known that for sufficiently strong pressure gradients the form of (1) changes (seeNickels 2004) Patel (1965) quantifies the effect of pressure gradients using the non-dimensional pressure gradient parameter1

p+x =ν

ρU3τ

dp

dx (8)

The error associated with using a Preston tube in pressure gradients is quantified by Patel(1965) and is given by the following inequalities

1 Adverse pressure gradient

Max Error 3 0 lt p+x lt 001 andUτd

νle 200 (9a)

Max Error 6 0 lt p+x lt 0015 andUτd

νle 250 (9b)

2 Favourable pressure gradient

Max Error 3 minus0005 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10a)

Max Error 6 minus0007 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10b)

The pressure gradient data are presented in Section 44 and were found to fall within thelimits of (9a) and (10a) indicating that the skin-friction coefficients are valid to withinplusmn3 This accuracy is similar to the alternative direct skin-friction measuring techniqueswhich typically achieve an accuracy of plusmn4 (Fernholz et al 1996)

The effect of model spanwise curvature on (4)-(6) is not quantified A reasonableassumption is that since the boundary layer thickness is much less than the model diameterthe effect of spanwise model curvature can be neglected

The Preston-tube method as outlined above requires that the boundary layer is in aturbulent state For this reason the method cannot be used to infer the skin friction atlocations were the boundary layer is in a laminar state However the ∆p values read by thePreston tube can be used to determine where laminar-to-turbulent transition occurs Theregion of transition is associated with a discontinuity in ∆p when plotted as a functionof streamwise coordinate x as shown by Erm amp Joubert (1991)

1for clarity we have adopted the notation for the pressure gradient parameter used by Nickels (2004)Patel (1965) uses the symbol ∆

6 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 4 LSWT Layout see Erm (2003)

3 Test Program

In this preliminary investigation four different tripping devices were used to investigatethe effect of the device on the skin-friction profile of a generic sub-scale submarine modelTests were conducted both with and without the tripping devices at a range of nominalfree-stream velocities Uinfin ranging from Uinfin = 40 to 70 ms to assess their effectivenessin tripping the boundary layer

31 Test Facility

The Low-Speed Wind Tunnel at DSTO is a closed circuit continuous flow tunnel with acontraction ratio of 41 The test section has an irregular octagonal shape with a heightof 213 m a width of 274 m and a length of 6553 m with a longitudinal turbulenceintensity of approximately 04 in the region where the models are tested (see Erm2003) An outline of the plan of the wind tunnel is shown in Figure 4 Free-streamvelocities were measured using static pressure rings at the upstream and downstreamends of the contraction A Pitot-static probe mounted on the side wall near the front ofthe working section was used to provide an independent measurement of the free-streamvelocity

32 Test Model

The sub-scale submarine model utilised in these tests is referred to as the Joubert modelsince the geometry is based on the work of Joubert (2004) and Joubert (2006) as well asLoid amp Bystrom (1983) The model was designed for the purpose of experimental and

UNCLASSIFIED 7

DSTOndashTRndash2898 UNCLASSIFIED

1

2 345

6 7 8 91011

12 13 141516

17 181920

212223

24 252627

28 29 303132

33 34

35

Top view

Side view

Figure 5 Schematic of scale model showing static-pressure port locations green and redmarkers represent the starboard and port static-pressure ports respectively

numerical studies and has no full-scale equivalent While the full model includes a casingcentre fin and control surfaces all tests reported here were conducted on the axisymmetricbody shape only

The model was machined from aluminum and consists of an ellipsoidal nose a cylin-drical centre-body and a streamlined tail section At the design stage an N6 surface finishwas specified for the model which corresponds to a roughness of 08microm in waviness Af-ter manufacture the surface finish was checked using a Surface Roughness Indicator andthe finish was found to be better than the design specification The model was anodisedwhich increased the thickness of the natural oxide layer by about 10microm

The model is 1350 mm long with a maximum diameter of 185 mm and slendernessratio of 73 where the slenderness ratio is defined as hull length divided by maximumhull diameter The model contains 21 longitudinal static-pressure ports on the centre-lineof the upper surface and 14 lateral static-pressure ports offset to the port and starboardsides of the upper surface centre-line Figure 5 shows the stream-wise location of thestatic-pressure ports

The model was supported by a single pylon as shown in Figure 6 All tests were carriedout at zero angle of yaw and zero angle of pitch The origin of the body coordinate systemis located at the nose of the submarine model The x-axis corresponds to the axis ofsymmetry of the model

8 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 6 Submarine model mounted in LSWT showing pylon support and pitch controlarm

UNCLASSIFIED 9

DSTOndashTRndash2898 UNCLASSIFIED

Table 1 Details of tripping devices where the Reynolds number is based on the height ofthe device The minimum Reynolds number and maximum Reynolds number correspondto nominal freestream velocities of Uinfin = 40 ms and Uinfin = 70 ms respectively where his the height of the grit and w is the width of the grit

Device Dimensions (mm) RedT (min) RedT (max)

Wire 1 dT = 01 281 496Wire 2 dT = 02 577 1015Wire 3 dT = 05 1443 256680 Grit h = 021 w = 3 605 1073

33 Tripping Devices

In this work four tripping devices were tested and consisted of circular wires with diame-ters dT = 01 02 and 05 mm as well as a distributed silicon carbide grit of size 80 havinga width of 3 mm The circular wires were bent to conform to the local diameter of thesubmarine and then attached with ldquosuper-gluerdquo such that there was no gap between thewire and the model surface Figure 7 The silicon carbide grit is prepared by distributinga layer of grit on double-sided sticky tape the tape is then adhered to the submarineFigure 8 The tripping devices were attached to the submarine model circumferentiallylocated at a streamwise coordinate of x = 675 mm measured from the nose of the sub-marine which corresponds to 5 of the total model length The dimensions of the tripdevices along with the Reynolds number range of the trip devices are summarised inTable 1 Note that the Reynolds number of the trip device is defined as RedT = U1dT νwhere for the case of the 80 grit dT is replaced by the grit height h

34 Pressure Scanners

Pressure Systems Incorporated (PSI) brand pressure scanners were used to measure allstatic and total pressures The pressure scanners are differential pressure measurementunits consisting of an array of silicon piezoresistive pressure sensors one for each pressureport The outputs of the sensors are electronically multiplexed through a single on-boardinstrumentation amplifier using binary addressing The scanners include a two-positioncalibration manifold actuated by momentary pulses of control pressures In the calibrateposition all sensors are connected to a common calibration pressure port A series ofaccurately-measured pressures is applied through this port to characterize the sensorsProper and periodic on-line calibration maintains static errors within plusmn003 or betterof the full-scale pressure range

The pressure scanners are controlled and sampled using a PSI 8400 electronic measure-ment system It is a modular parallel processing system for high-speed pressure scanningat up to 20000 measurements per second and allows the use of digitally temperaturecompensated pressure scanners

Two differential pressure scanners were used in the experiments All pressures aremeasured relative to the free-stream static pressure pinfin as measured by the referencefree-stream Pitot-static probe Each pressure scanner contained 32 ports The full-scale

10 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 7 Location of trip wire

Figure 8 Photo showing the 3 mm wide band of 80 grit transition strip

UNCLASSIFIED 11

DSTOndashTRndash2898 UNCLASSIFIED

pressure range of the scanners is 249 kPa (ldquo10 inches-of-water scannerrdquo) and 689 kPa(ldquo1 psi scannerrdquo) The 689 kPa scanner was used to read the static pressure at the longi-tudinal ports as well as the output from the Preston tube and the Pitot-static probe

For the purpose of cross-checking and for redundancy the Preston tube was connectedto two independent ports of the 689 kPa scanner and the two readings averaged For thisscanner pressures could be read to an accuracy of 6890 times 00003 Pa ie about 2 Pa Theminimum ∆p measured by the Preston tube was 145 Pa which gives a pressure scannerresolution of 14 However this minimum ∆p was recorded for a location where thePreston tube was in a laminar boundary layer and such data is only useful in a qualitativesense (see Section 2) For locations were the boundary layer is turbulent the minimum ∆pwas 340 Pa which gives a pressure scanner resolution of 06 The 249 kPa scanner wasused mainly to acquire the static pressures at the lateral ports

35 Data Acquisition Software

A software package called ImPressOne was used which communicates with the PSI 8400and displays and acquires the pressure data for the model under test For the staticpressure measurements 100 readings were acquired at each pressure port at a samplingrate of 20 Hz For the Preston-tube measurements the sample rate was increased and100 samples were acquired at each pressure port at a sampling rate of 50 Hz for eachfree-stream velocity

36 Experimental Procedure

The hull was tested with each of the selected tripping devices listed in Table 1 as wellas without a tripping device resulting in five different test configurations For each testconfiguration the static pressures were initially acquired for that particular configurationfollowed by the Preston-tube measurements

A Preston tube having a diameter of 06 mm was attached to the surface of the modelusing both plasticine and tape to ensure that the tube was positioned as flat as possibleon the surface of the model as shown in Figure 9 Preston-tube measurement were takenon the upper surface of the submarine model along a line directly above the centre-lineof the model For the dT = 02 and 05 mm wires and the grit case measurements weretaken from x = 73 mm to x = 1065 mm for a total of 18 stations For the dT = 01 mmwire measurements were limited to 3 stations between x = 305 mm and x = 442 mmThe stream-wise coordinates for the Preston tube measurements are given in the Table 2Data were acquired for a range of free-stream velocities from 40 to 70 ms in incrementsof 5 ms

For each nominal velocity the corresponding model Reynolds number was calcu-lated assuming standard temperature and atmospheric pressure conditions 20C and101 325 Pa respectively For each given test the temperature and static pressure of theair within the test section were logged and the air density and viscosity were calculatedTo account for daily variations in temperature and atmospheric pressure the freestream

12 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Flow direction

Figure 9 Preston tube located on the centre-line of the upper-surface of submarine

velocity was adjusted to ensure that the model Reynolds number remained constant foreach given nominal velocity condition as shown in Table 3

Table 2 Skin-friction measurement stations Where applicable the corresponding staticport number is given For the dT = 01 mm wire measurements were only taken at stations3050 3600 as well as an additional station at x = 4425 mm

xmm 731 787 843 900 1125 1350 1575 1800 2150Static port - - - 6 - 7 - 8 -

xmm 2500 3050 3600 5250 7000 8700 9500 10100 10650Static port 9 - 12 13 14 17 18 21 24

Table 3 Reynolds numbers (based on submarine length 135 m) corresponding to thenominal free-stream velocities

Nominal Uinfin 40 45 50 55 60 65 70 msRe 358 403 448 493 537 582 627 times106

37 Data Reduction

The static pressure readings from the pressure ports were converted to pressure coefficientsusing the relationship

Cp =ps minus pinfinpt minus pinfin

(11)

where pinfin is the reference free-stream static pressure pt is the reference free-stream totalpressure and ps is the static pressure on the surface of the submarine model

As explained in Section 34 all Preston tube pressures are measured relative to the free-stream static pressure In order to apply the Preston tube calibration (4)-(6) the loggedPreston-tube pressure differences (ie pp minus pinfin) must first be converted to a ∆p = pp minus ps

UNCLASSIFIED 13

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 16: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

13 Empirical Expressions to Determine Sizes of TrippingDevices

Researchers have proposed different empirical expressions for determining the size of deviceto use to trip the flow The relationships incorporate parameters including the height ofthe tripping device dT the velocity at the edge of the boundary layer U1 the velocity inthe undisturbed boundary layer at the top of the device Ud and the wall friction velocityevaluated at the device Uτ The friction velocity is defined by τ0 = ρU2

τ where τ0 is thesurface shear stress and ρ is the fluid density Recommendations for fully-effective trippingcover quite a wide range Tani et al (1940) proposed the criterion UτdT ν = 13 Fage ampPreston (1941) proposed UτdT ν = 20 Braslow amp Knox (1958) proposed UddT ν = 600and Gibbings (1959) proposed U1dT ν = 826 It should be noted that the criterion ofGibbings (1959) is based on a review of many data sets included those of Tani amp Sato(1956) and Fage amp Preston (1941) Gibbings (1959) expresses the Tani amp Sato (1956)and Fage amp Preston (1941) criteria as Reynolds numbers based on the freestream velocitywhich gives values of U1dT ν = 600 and 840 respectively The criterion given aboverepresent minimum values of the tripping device Reynolds number required to correctlytrip the boundary layer and agree with the results of Erm amp Joubert (1991)

An analysis of the literature for tests done on bodies of revolution indicated that thereis no consistent approach for selecting the size and type of device to use on such bodiesAppendix A gives details of devices used by different investigators for bodies of revolutiontogether with other experimental information Based on the freestream velocity and tripheight the Reynolds numbers of the trip devices given in Appendix A range from 200 to40 times 103 For the present investigation the approach used to establish the effects thatdifferent devices had on tripping laminar boundary layers was similar to that used byErm amp Joubert (1991) for a smooth flat plate in a zero pressure gradient Using theirtechnique it is possible to establish the size and type of tripping device to be used for agiven velocity to obtain correctly stimulated turbulent boundary layers

2 Preston-Tube Method of Measuring

Skin-Friction Coefficients

Skin-friction coefficients in a turbulent boundary layer flowing over a smooth surface canbe measured in a number of different ways (Fernholz et al 1996) including using Prestontubes (Preston 1954) from velocity profiles and using devices mounted flush with thesurface of a model Of the alternative approaches the Preston-tube method is convenientand is widely used The method makes use of a simple Pitot tube placed on the surfaceof a body and when used this way it is termed a Preston tube The method depends onan underlining assumption that in the region adjacent to the surface the flow is primarilydetermined by the surface shear stress and the properties of the fluid and is independentof factors such as pressure gradient and surface curvature The assumption implies thatthe velocity profile in a turbulent boundary layer adjacent to the surface is given by

U

Uτ= f

(Uτy

ν

)(1)

4 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

where U is the local stream-wise velocity Uτ is the friction velocity f is a universalfunction y is the wall normal coordinate and ν is the kinematic viscosity Equation (1) isoften referred to as the ldquolaw of the wallrdquo (Coles 1956)

A Pitot tube placed on the wall will measure a pressure relative to the wall staticpressure of ∆p = ρU22 at an effective coordinate y = c0d where d is the outer diameterof the Pitot tube and c0 is an unknown constant Substituting the values U =

radic(2∆pρ)

and y = cod into (1) yields a relationship between the wall shear stress fluid propertiesPreston-tube pressure difference and the tube diameter which is given by

2∆p

ρUτ2 =

[f

(Uτ c0d

ν

)]2 (2)

Alternatively for the purpose of measuring skin friction (2) can be expressed more con-veniently in the form

τ0d2

4ρν2= F

(∆pd2

4ρν2

)(3)

where c0 has been absorbed into the function F The function F represents the ldquocalibra-tionrdquo function for a Preston tube and several experimentally derived forms exist in theliterature (see Preston 1954 Patel 1965 Zagarola et al 2001) Generally the calibrationis determined by placing the Preston tube in a pipe flow where the wall shear stress (orfriction factor) can be determined accurately by measuring the pressure gradient in thepipe

For the data presented in this report the calibration of Patel (1965) was used todetermine the wall shear stress The calibration curve of Patel (1965) is given as follows

xlowast =ylowast + 2 log10(195ylowast + 410) for 55 ltUτd

2νlt 800 (4)

ylowast =08287 minus 01381xlowast + 01437xlowast2 minus 0006xlowast3 for 56 ltUτd

2νlt 55 and (5)

ylowast =1

2xlowast + 0037 for

Uτd

2νlt 56 (6)

where

xlowast = log10

(∆pd2

4ρν2

)and ylowast = log10

(τ0d

2

4ρν2

)

The local skin friction coefficient Cf is then found using

Cf =τ0

12ρU

21

(7)

where U1 is the streamwise velocity at the edge of the boundary layer

The calibration given by (4)-(6) is valid only for a hydrodynamically smooth surfaceA surface is considered hydrodynamically smooth provided that the height of surfaceroughness elements remain less than 5νUτ (Jimenez 2004) The minimum value of 5νUτthat was measured was approximately 4microm and the measured surface finish was found tobe an order of magnitude less than this value (Section 32) Hence the requirement of ahydrodynamically smooth surface is satisfied for this experiment

UNCLASSIFIED 5

DSTOndashTRndash2898 UNCLASSIFIED

The fundamental requirement for using a Preston tube is that the boundary layer isin a turbulent state and that the dimension of the Preston tube is such that it remainswithin the region where (1) is valid (ie from (4) Uτdν lt 1600) The diameter of thePreston tube for all experiments was d = 06 mm and this ensured that Uτdν remainedless than 1600 well within the range of the calibration (4)

It is known that for sufficiently strong pressure gradients the form of (1) changes (seeNickels 2004) Patel (1965) quantifies the effect of pressure gradients using the non-dimensional pressure gradient parameter1

p+x =ν

ρU3τ

dp

dx (8)

The error associated with using a Preston tube in pressure gradients is quantified by Patel(1965) and is given by the following inequalities

1 Adverse pressure gradient

Max Error 3 0 lt p+x lt 001 andUτd

νle 200 (9a)

Max Error 6 0 lt p+x lt 0015 andUτd

νle 250 (9b)

2 Favourable pressure gradient

Max Error 3 minus0005 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10a)

Max Error 6 minus0007 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10b)

The pressure gradient data are presented in Section 44 and were found to fall within thelimits of (9a) and (10a) indicating that the skin-friction coefficients are valid to withinplusmn3 This accuracy is similar to the alternative direct skin-friction measuring techniqueswhich typically achieve an accuracy of plusmn4 (Fernholz et al 1996)

The effect of model spanwise curvature on (4)-(6) is not quantified A reasonableassumption is that since the boundary layer thickness is much less than the model diameterthe effect of spanwise model curvature can be neglected

The Preston-tube method as outlined above requires that the boundary layer is in aturbulent state For this reason the method cannot be used to infer the skin friction atlocations were the boundary layer is in a laminar state However the ∆p values read by thePreston tube can be used to determine where laminar-to-turbulent transition occurs Theregion of transition is associated with a discontinuity in ∆p when plotted as a functionof streamwise coordinate x as shown by Erm amp Joubert (1991)

1for clarity we have adopted the notation for the pressure gradient parameter used by Nickels (2004)Patel (1965) uses the symbol ∆

6 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 4 LSWT Layout see Erm (2003)

3 Test Program

In this preliminary investigation four different tripping devices were used to investigatethe effect of the device on the skin-friction profile of a generic sub-scale submarine modelTests were conducted both with and without the tripping devices at a range of nominalfree-stream velocities Uinfin ranging from Uinfin = 40 to 70 ms to assess their effectivenessin tripping the boundary layer

31 Test Facility

The Low-Speed Wind Tunnel at DSTO is a closed circuit continuous flow tunnel with acontraction ratio of 41 The test section has an irregular octagonal shape with a heightof 213 m a width of 274 m and a length of 6553 m with a longitudinal turbulenceintensity of approximately 04 in the region where the models are tested (see Erm2003) An outline of the plan of the wind tunnel is shown in Figure 4 Free-streamvelocities were measured using static pressure rings at the upstream and downstreamends of the contraction A Pitot-static probe mounted on the side wall near the front ofthe working section was used to provide an independent measurement of the free-streamvelocity

32 Test Model

The sub-scale submarine model utilised in these tests is referred to as the Joubert modelsince the geometry is based on the work of Joubert (2004) and Joubert (2006) as well asLoid amp Bystrom (1983) The model was designed for the purpose of experimental and

UNCLASSIFIED 7

DSTOndashTRndash2898 UNCLASSIFIED

1

2 345

6 7 8 91011

12 13 141516

17 181920

212223

24 252627

28 29 303132

33 34

35

Top view

Side view

Figure 5 Schematic of scale model showing static-pressure port locations green and redmarkers represent the starboard and port static-pressure ports respectively

numerical studies and has no full-scale equivalent While the full model includes a casingcentre fin and control surfaces all tests reported here were conducted on the axisymmetricbody shape only

The model was machined from aluminum and consists of an ellipsoidal nose a cylin-drical centre-body and a streamlined tail section At the design stage an N6 surface finishwas specified for the model which corresponds to a roughness of 08microm in waviness Af-ter manufacture the surface finish was checked using a Surface Roughness Indicator andthe finish was found to be better than the design specification The model was anodisedwhich increased the thickness of the natural oxide layer by about 10microm

The model is 1350 mm long with a maximum diameter of 185 mm and slendernessratio of 73 where the slenderness ratio is defined as hull length divided by maximumhull diameter The model contains 21 longitudinal static-pressure ports on the centre-lineof the upper surface and 14 lateral static-pressure ports offset to the port and starboardsides of the upper surface centre-line Figure 5 shows the stream-wise location of thestatic-pressure ports

The model was supported by a single pylon as shown in Figure 6 All tests were carriedout at zero angle of yaw and zero angle of pitch The origin of the body coordinate systemis located at the nose of the submarine model The x-axis corresponds to the axis ofsymmetry of the model

8 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 6 Submarine model mounted in LSWT showing pylon support and pitch controlarm

UNCLASSIFIED 9

DSTOndashTRndash2898 UNCLASSIFIED

Table 1 Details of tripping devices where the Reynolds number is based on the height ofthe device The minimum Reynolds number and maximum Reynolds number correspondto nominal freestream velocities of Uinfin = 40 ms and Uinfin = 70 ms respectively where his the height of the grit and w is the width of the grit

Device Dimensions (mm) RedT (min) RedT (max)

Wire 1 dT = 01 281 496Wire 2 dT = 02 577 1015Wire 3 dT = 05 1443 256680 Grit h = 021 w = 3 605 1073

33 Tripping Devices

In this work four tripping devices were tested and consisted of circular wires with diame-ters dT = 01 02 and 05 mm as well as a distributed silicon carbide grit of size 80 havinga width of 3 mm The circular wires were bent to conform to the local diameter of thesubmarine and then attached with ldquosuper-gluerdquo such that there was no gap between thewire and the model surface Figure 7 The silicon carbide grit is prepared by distributinga layer of grit on double-sided sticky tape the tape is then adhered to the submarineFigure 8 The tripping devices were attached to the submarine model circumferentiallylocated at a streamwise coordinate of x = 675 mm measured from the nose of the sub-marine which corresponds to 5 of the total model length The dimensions of the tripdevices along with the Reynolds number range of the trip devices are summarised inTable 1 Note that the Reynolds number of the trip device is defined as RedT = U1dT νwhere for the case of the 80 grit dT is replaced by the grit height h

34 Pressure Scanners

Pressure Systems Incorporated (PSI) brand pressure scanners were used to measure allstatic and total pressures The pressure scanners are differential pressure measurementunits consisting of an array of silicon piezoresistive pressure sensors one for each pressureport The outputs of the sensors are electronically multiplexed through a single on-boardinstrumentation amplifier using binary addressing The scanners include a two-positioncalibration manifold actuated by momentary pulses of control pressures In the calibrateposition all sensors are connected to a common calibration pressure port A series ofaccurately-measured pressures is applied through this port to characterize the sensorsProper and periodic on-line calibration maintains static errors within plusmn003 or betterof the full-scale pressure range

The pressure scanners are controlled and sampled using a PSI 8400 electronic measure-ment system It is a modular parallel processing system for high-speed pressure scanningat up to 20000 measurements per second and allows the use of digitally temperaturecompensated pressure scanners

Two differential pressure scanners were used in the experiments All pressures aremeasured relative to the free-stream static pressure pinfin as measured by the referencefree-stream Pitot-static probe Each pressure scanner contained 32 ports The full-scale

10 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 7 Location of trip wire

Figure 8 Photo showing the 3 mm wide band of 80 grit transition strip

UNCLASSIFIED 11

DSTOndashTRndash2898 UNCLASSIFIED

pressure range of the scanners is 249 kPa (ldquo10 inches-of-water scannerrdquo) and 689 kPa(ldquo1 psi scannerrdquo) The 689 kPa scanner was used to read the static pressure at the longi-tudinal ports as well as the output from the Preston tube and the Pitot-static probe

For the purpose of cross-checking and for redundancy the Preston tube was connectedto two independent ports of the 689 kPa scanner and the two readings averaged For thisscanner pressures could be read to an accuracy of 6890 times 00003 Pa ie about 2 Pa Theminimum ∆p measured by the Preston tube was 145 Pa which gives a pressure scannerresolution of 14 However this minimum ∆p was recorded for a location where thePreston tube was in a laminar boundary layer and such data is only useful in a qualitativesense (see Section 2) For locations were the boundary layer is turbulent the minimum ∆pwas 340 Pa which gives a pressure scanner resolution of 06 The 249 kPa scanner wasused mainly to acquire the static pressures at the lateral ports

35 Data Acquisition Software

A software package called ImPressOne was used which communicates with the PSI 8400and displays and acquires the pressure data for the model under test For the staticpressure measurements 100 readings were acquired at each pressure port at a samplingrate of 20 Hz For the Preston-tube measurements the sample rate was increased and100 samples were acquired at each pressure port at a sampling rate of 50 Hz for eachfree-stream velocity

36 Experimental Procedure

The hull was tested with each of the selected tripping devices listed in Table 1 as wellas without a tripping device resulting in five different test configurations For each testconfiguration the static pressures were initially acquired for that particular configurationfollowed by the Preston-tube measurements

A Preston tube having a diameter of 06 mm was attached to the surface of the modelusing both plasticine and tape to ensure that the tube was positioned as flat as possibleon the surface of the model as shown in Figure 9 Preston-tube measurement were takenon the upper surface of the submarine model along a line directly above the centre-lineof the model For the dT = 02 and 05 mm wires and the grit case measurements weretaken from x = 73 mm to x = 1065 mm for a total of 18 stations For the dT = 01 mmwire measurements were limited to 3 stations between x = 305 mm and x = 442 mmThe stream-wise coordinates for the Preston tube measurements are given in the Table 2Data were acquired for a range of free-stream velocities from 40 to 70 ms in incrementsof 5 ms

For each nominal velocity the corresponding model Reynolds number was calcu-lated assuming standard temperature and atmospheric pressure conditions 20C and101 325 Pa respectively For each given test the temperature and static pressure of theair within the test section were logged and the air density and viscosity were calculatedTo account for daily variations in temperature and atmospheric pressure the freestream

12 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Flow direction

Figure 9 Preston tube located on the centre-line of the upper-surface of submarine

velocity was adjusted to ensure that the model Reynolds number remained constant foreach given nominal velocity condition as shown in Table 3

Table 2 Skin-friction measurement stations Where applicable the corresponding staticport number is given For the dT = 01 mm wire measurements were only taken at stations3050 3600 as well as an additional station at x = 4425 mm

xmm 731 787 843 900 1125 1350 1575 1800 2150Static port - - - 6 - 7 - 8 -

xmm 2500 3050 3600 5250 7000 8700 9500 10100 10650Static port 9 - 12 13 14 17 18 21 24

Table 3 Reynolds numbers (based on submarine length 135 m) corresponding to thenominal free-stream velocities

Nominal Uinfin 40 45 50 55 60 65 70 msRe 358 403 448 493 537 582 627 times106

37 Data Reduction

The static pressure readings from the pressure ports were converted to pressure coefficientsusing the relationship

Cp =ps minus pinfinpt minus pinfin

(11)

where pinfin is the reference free-stream static pressure pt is the reference free-stream totalpressure and ps is the static pressure on the surface of the submarine model

As explained in Section 34 all Preston tube pressures are measured relative to the free-stream static pressure In order to apply the Preston tube calibration (4)-(6) the loggedPreston-tube pressure differences (ie pp minus pinfin) must first be converted to a ∆p = pp minus ps

UNCLASSIFIED 13

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 17: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

where U is the local stream-wise velocity Uτ is the friction velocity f is a universalfunction y is the wall normal coordinate and ν is the kinematic viscosity Equation (1) isoften referred to as the ldquolaw of the wallrdquo (Coles 1956)

A Pitot tube placed on the wall will measure a pressure relative to the wall staticpressure of ∆p = ρU22 at an effective coordinate y = c0d where d is the outer diameterof the Pitot tube and c0 is an unknown constant Substituting the values U =

radic(2∆pρ)

and y = cod into (1) yields a relationship between the wall shear stress fluid propertiesPreston-tube pressure difference and the tube diameter which is given by

2∆p

ρUτ2 =

[f

(Uτ c0d

ν

)]2 (2)

Alternatively for the purpose of measuring skin friction (2) can be expressed more con-veniently in the form

τ0d2

4ρν2= F

(∆pd2

4ρν2

)(3)

where c0 has been absorbed into the function F The function F represents the ldquocalibra-tionrdquo function for a Preston tube and several experimentally derived forms exist in theliterature (see Preston 1954 Patel 1965 Zagarola et al 2001) Generally the calibrationis determined by placing the Preston tube in a pipe flow where the wall shear stress (orfriction factor) can be determined accurately by measuring the pressure gradient in thepipe

For the data presented in this report the calibration of Patel (1965) was used todetermine the wall shear stress The calibration curve of Patel (1965) is given as follows

xlowast =ylowast + 2 log10(195ylowast + 410) for 55 ltUτd

2νlt 800 (4)

ylowast =08287 minus 01381xlowast + 01437xlowast2 minus 0006xlowast3 for 56 ltUτd

2νlt 55 and (5)

ylowast =1

2xlowast + 0037 for

Uτd

2νlt 56 (6)

where

xlowast = log10

(∆pd2

4ρν2

)and ylowast = log10

(τ0d

2

4ρν2

)

The local skin friction coefficient Cf is then found using

Cf =τ0

12ρU

21

(7)

where U1 is the streamwise velocity at the edge of the boundary layer

The calibration given by (4)-(6) is valid only for a hydrodynamically smooth surfaceA surface is considered hydrodynamically smooth provided that the height of surfaceroughness elements remain less than 5νUτ (Jimenez 2004) The minimum value of 5νUτthat was measured was approximately 4microm and the measured surface finish was found tobe an order of magnitude less than this value (Section 32) Hence the requirement of ahydrodynamically smooth surface is satisfied for this experiment

UNCLASSIFIED 5

DSTOndashTRndash2898 UNCLASSIFIED

The fundamental requirement for using a Preston tube is that the boundary layer isin a turbulent state and that the dimension of the Preston tube is such that it remainswithin the region where (1) is valid (ie from (4) Uτdν lt 1600) The diameter of thePreston tube for all experiments was d = 06 mm and this ensured that Uτdν remainedless than 1600 well within the range of the calibration (4)

It is known that for sufficiently strong pressure gradients the form of (1) changes (seeNickels 2004) Patel (1965) quantifies the effect of pressure gradients using the non-dimensional pressure gradient parameter1

p+x =ν

ρU3τ

dp

dx (8)

The error associated with using a Preston tube in pressure gradients is quantified by Patel(1965) and is given by the following inequalities

1 Adverse pressure gradient

Max Error 3 0 lt p+x lt 001 andUτd

νle 200 (9a)

Max Error 6 0 lt p+x lt 0015 andUτd

νle 250 (9b)

2 Favourable pressure gradient

Max Error 3 minus0005 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10a)

Max Error 6 minus0007 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10b)

The pressure gradient data are presented in Section 44 and were found to fall within thelimits of (9a) and (10a) indicating that the skin-friction coefficients are valid to withinplusmn3 This accuracy is similar to the alternative direct skin-friction measuring techniqueswhich typically achieve an accuracy of plusmn4 (Fernholz et al 1996)

The effect of model spanwise curvature on (4)-(6) is not quantified A reasonableassumption is that since the boundary layer thickness is much less than the model diameterthe effect of spanwise model curvature can be neglected

The Preston-tube method as outlined above requires that the boundary layer is in aturbulent state For this reason the method cannot be used to infer the skin friction atlocations were the boundary layer is in a laminar state However the ∆p values read by thePreston tube can be used to determine where laminar-to-turbulent transition occurs Theregion of transition is associated with a discontinuity in ∆p when plotted as a functionof streamwise coordinate x as shown by Erm amp Joubert (1991)

1for clarity we have adopted the notation for the pressure gradient parameter used by Nickels (2004)Patel (1965) uses the symbol ∆

6 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 4 LSWT Layout see Erm (2003)

3 Test Program

In this preliminary investigation four different tripping devices were used to investigatethe effect of the device on the skin-friction profile of a generic sub-scale submarine modelTests were conducted both with and without the tripping devices at a range of nominalfree-stream velocities Uinfin ranging from Uinfin = 40 to 70 ms to assess their effectivenessin tripping the boundary layer

31 Test Facility

The Low-Speed Wind Tunnel at DSTO is a closed circuit continuous flow tunnel with acontraction ratio of 41 The test section has an irregular octagonal shape with a heightof 213 m a width of 274 m and a length of 6553 m with a longitudinal turbulenceintensity of approximately 04 in the region where the models are tested (see Erm2003) An outline of the plan of the wind tunnel is shown in Figure 4 Free-streamvelocities were measured using static pressure rings at the upstream and downstreamends of the contraction A Pitot-static probe mounted on the side wall near the front ofthe working section was used to provide an independent measurement of the free-streamvelocity

32 Test Model

The sub-scale submarine model utilised in these tests is referred to as the Joubert modelsince the geometry is based on the work of Joubert (2004) and Joubert (2006) as well asLoid amp Bystrom (1983) The model was designed for the purpose of experimental and

UNCLASSIFIED 7

DSTOndashTRndash2898 UNCLASSIFIED

1

2 345

6 7 8 91011

12 13 141516

17 181920

212223

24 252627

28 29 303132

33 34

35

Top view

Side view

Figure 5 Schematic of scale model showing static-pressure port locations green and redmarkers represent the starboard and port static-pressure ports respectively

numerical studies and has no full-scale equivalent While the full model includes a casingcentre fin and control surfaces all tests reported here were conducted on the axisymmetricbody shape only

The model was machined from aluminum and consists of an ellipsoidal nose a cylin-drical centre-body and a streamlined tail section At the design stage an N6 surface finishwas specified for the model which corresponds to a roughness of 08microm in waviness Af-ter manufacture the surface finish was checked using a Surface Roughness Indicator andthe finish was found to be better than the design specification The model was anodisedwhich increased the thickness of the natural oxide layer by about 10microm

The model is 1350 mm long with a maximum diameter of 185 mm and slendernessratio of 73 where the slenderness ratio is defined as hull length divided by maximumhull diameter The model contains 21 longitudinal static-pressure ports on the centre-lineof the upper surface and 14 lateral static-pressure ports offset to the port and starboardsides of the upper surface centre-line Figure 5 shows the stream-wise location of thestatic-pressure ports

The model was supported by a single pylon as shown in Figure 6 All tests were carriedout at zero angle of yaw and zero angle of pitch The origin of the body coordinate systemis located at the nose of the submarine model The x-axis corresponds to the axis ofsymmetry of the model

8 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 6 Submarine model mounted in LSWT showing pylon support and pitch controlarm

UNCLASSIFIED 9

DSTOndashTRndash2898 UNCLASSIFIED

Table 1 Details of tripping devices where the Reynolds number is based on the height ofthe device The minimum Reynolds number and maximum Reynolds number correspondto nominal freestream velocities of Uinfin = 40 ms and Uinfin = 70 ms respectively where his the height of the grit and w is the width of the grit

Device Dimensions (mm) RedT (min) RedT (max)

Wire 1 dT = 01 281 496Wire 2 dT = 02 577 1015Wire 3 dT = 05 1443 256680 Grit h = 021 w = 3 605 1073

33 Tripping Devices

In this work four tripping devices were tested and consisted of circular wires with diame-ters dT = 01 02 and 05 mm as well as a distributed silicon carbide grit of size 80 havinga width of 3 mm The circular wires were bent to conform to the local diameter of thesubmarine and then attached with ldquosuper-gluerdquo such that there was no gap between thewire and the model surface Figure 7 The silicon carbide grit is prepared by distributinga layer of grit on double-sided sticky tape the tape is then adhered to the submarineFigure 8 The tripping devices were attached to the submarine model circumferentiallylocated at a streamwise coordinate of x = 675 mm measured from the nose of the sub-marine which corresponds to 5 of the total model length The dimensions of the tripdevices along with the Reynolds number range of the trip devices are summarised inTable 1 Note that the Reynolds number of the trip device is defined as RedT = U1dT νwhere for the case of the 80 grit dT is replaced by the grit height h

34 Pressure Scanners

Pressure Systems Incorporated (PSI) brand pressure scanners were used to measure allstatic and total pressures The pressure scanners are differential pressure measurementunits consisting of an array of silicon piezoresistive pressure sensors one for each pressureport The outputs of the sensors are electronically multiplexed through a single on-boardinstrumentation amplifier using binary addressing The scanners include a two-positioncalibration manifold actuated by momentary pulses of control pressures In the calibrateposition all sensors are connected to a common calibration pressure port A series ofaccurately-measured pressures is applied through this port to characterize the sensorsProper and periodic on-line calibration maintains static errors within plusmn003 or betterof the full-scale pressure range

The pressure scanners are controlled and sampled using a PSI 8400 electronic measure-ment system It is a modular parallel processing system for high-speed pressure scanningat up to 20000 measurements per second and allows the use of digitally temperaturecompensated pressure scanners

Two differential pressure scanners were used in the experiments All pressures aremeasured relative to the free-stream static pressure pinfin as measured by the referencefree-stream Pitot-static probe Each pressure scanner contained 32 ports The full-scale

10 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 7 Location of trip wire

Figure 8 Photo showing the 3 mm wide band of 80 grit transition strip

UNCLASSIFIED 11

DSTOndashTRndash2898 UNCLASSIFIED

pressure range of the scanners is 249 kPa (ldquo10 inches-of-water scannerrdquo) and 689 kPa(ldquo1 psi scannerrdquo) The 689 kPa scanner was used to read the static pressure at the longi-tudinal ports as well as the output from the Preston tube and the Pitot-static probe

For the purpose of cross-checking and for redundancy the Preston tube was connectedto two independent ports of the 689 kPa scanner and the two readings averaged For thisscanner pressures could be read to an accuracy of 6890 times 00003 Pa ie about 2 Pa Theminimum ∆p measured by the Preston tube was 145 Pa which gives a pressure scannerresolution of 14 However this minimum ∆p was recorded for a location where thePreston tube was in a laminar boundary layer and such data is only useful in a qualitativesense (see Section 2) For locations were the boundary layer is turbulent the minimum ∆pwas 340 Pa which gives a pressure scanner resolution of 06 The 249 kPa scanner wasused mainly to acquire the static pressures at the lateral ports

35 Data Acquisition Software

A software package called ImPressOne was used which communicates with the PSI 8400and displays and acquires the pressure data for the model under test For the staticpressure measurements 100 readings were acquired at each pressure port at a samplingrate of 20 Hz For the Preston-tube measurements the sample rate was increased and100 samples were acquired at each pressure port at a sampling rate of 50 Hz for eachfree-stream velocity

36 Experimental Procedure

The hull was tested with each of the selected tripping devices listed in Table 1 as wellas without a tripping device resulting in five different test configurations For each testconfiguration the static pressures were initially acquired for that particular configurationfollowed by the Preston-tube measurements

A Preston tube having a diameter of 06 mm was attached to the surface of the modelusing both plasticine and tape to ensure that the tube was positioned as flat as possibleon the surface of the model as shown in Figure 9 Preston-tube measurement were takenon the upper surface of the submarine model along a line directly above the centre-lineof the model For the dT = 02 and 05 mm wires and the grit case measurements weretaken from x = 73 mm to x = 1065 mm for a total of 18 stations For the dT = 01 mmwire measurements were limited to 3 stations between x = 305 mm and x = 442 mmThe stream-wise coordinates for the Preston tube measurements are given in the Table 2Data were acquired for a range of free-stream velocities from 40 to 70 ms in incrementsof 5 ms

For each nominal velocity the corresponding model Reynolds number was calcu-lated assuming standard temperature and atmospheric pressure conditions 20C and101 325 Pa respectively For each given test the temperature and static pressure of theair within the test section were logged and the air density and viscosity were calculatedTo account for daily variations in temperature and atmospheric pressure the freestream

12 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Flow direction

Figure 9 Preston tube located on the centre-line of the upper-surface of submarine

velocity was adjusted to ensure that the model Reynolds number remained constant foreach given nominal velocity condition as shown in Table 3

Table 2 Skin-friction measurement stations Where applicable the corresponding staticport number is given For the dT = 01 mm wire measurements were only taken at stations3050 3600 as well as an additional station at x = 4425 mm

xmm 731 787 843 900 1125 1350 1575 1800 2150Static port - - - 6 - 7 - 8 -

xmm 2500 3050 3600 5250 7000 8700 9500 10100 10650Static port 9 - 12 13 14 17 18 21 24

Table 3 Reynolds numbers (based on submarine length 135 m) corresponding to thenominal free-stream velocities

Nominal Uinfin 40 45 50 55 60 65 70 msRe 358 403 448 493 537 582 627 times106

37 Data Reduction

The static pressure readings from the pressure ports were converted to pressure coefficientsusing the relationship

Cp =ps minus pinfinpt minus pinfin

(11)

where pinfin is the reference free-stream static pressure pt is the reference free-stream totalpressure and ps is the static pressure on the surface of the submarine model

As explained in Section 34 all Preston tube pressures are measured relative to the free-stream static pressure In order to apply the Preston tube calibration (4)-(6) the loggedPreston-tube pressure differences (ie pp minus pinfin) must first be converted to a ∆p = pp minus ps

UNCLASSIFIED 13

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 18: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

The fundamental requirement for using a Preston tube is that the boundary layer isin a turbulent state and that the dimension of the Preston tube is such that it remainswithin the region where (1) is valid (ie from (4) Uτdν lt 1600) The diameter of thePreston tube for all experiments was d = 06 mm and this ensured that Uτdν remainedless than 1600 well within the range of the calibration (4)

It is known that for sufficiently strong pressure gradients the form of (1) changes (seeNickels 2004) Patel (1965) quantifies the effect of pressure gradients using the non-dimensional pressure gradient parameter1

p+x =ν

ρU3τ

dp

dx (8)

The error associated with using a Preston tube in pressure gradients is quantified by Patel(1965) and is given by the following inequalities

1 Adverse pressure gradient

Max Error 3 0 lt p+x lt 001 andUτd

νle 200 (9a)

Max Error 6 0 lt p+x lt 0015 andUτd

νle 250 (9b)

2 Favourable pressure gradient

Max Error 3 minus0005 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10a)

Max Error 6 minus0007 lt p+x lt 0 andUτd

νle 200 ddx(p+x ) lt 0 (10b)

The pressure gradient data are presented in Section 44 and were found to fall within thelimits of (9a) and (10a) indicating that the skin-friction coefficients are valid to withinplusmn3 This accuracy is similar to the alternative direct skin-friction measuring techniqueswhich typically achieve an accuracy of plusmn4 (Fernholz et al 1996)

The effect of model spanwise curvature on (4)-(6) is not quantified A reasonableassumption is that since the boundary layer thickness is much less than the model diameterthe effect of spanwise model curvature can be neglected

The Preston-tube method as outlined above requires that the boundary layer is in aturbulent state For this reason the method cannot be used to infer the skin friction atlocations were the boundary layer is in a laminar state However the ∆p values read by thePreston tube can be used to determine where laminar-to-turbulent transition occurs Theregion of transition is associated with a discontinuity in ∆p when plotted as a functionof streamwise coordinate x as shown by Erm amp Joubert (1991)

1for clarity we have adopted the notation for the pressure gradient parameter used by Nickels (2004)Patel (1965) uses the symbol ∆

6 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 4 LSWT Layout see Erm (2003)

3 Test Program

In this preliminary investigation four different tripping devices were used to investigatethe effect of the device on the skin-friction profile of a generic sub-scale submarine modelTests were conducted both with and without the tripping devices at a range of nominalfree-stream velocities Uinfin ranging from Uinfin = 40 to 70 ms to assess their effectivenessin tripping the boundary layer

31 Test Facility

The Low-Speed Wind Tunnel at DSTO is a closed circuit continuous flow tunnel with acontraction ratio of 41 The test section has an irregular octagonal shape with a heightof 213 m a width of 274 m and a length of 6553 m with a longitudinal turbulenceintensity of approximately 04 in the region where the models are tested (see Erm2003) An outline of the plan of the wind tunnel is shown in Figure 4 Free-streamvelocities were measured using static pressure rings at the upstream and downstreamends of the contraction A Pitot-static probe mounted on the side wall near the front ofthe working section was used to provide an independent measurement of the free-streamvelocity

32 Test Model

The sub-scale submarine model utilised in these tests is referred to as the Joubert modelsince the geometry is based on the work of Joubert (2004) and Joubert (2006) as well asLoid amp Bystrom (1983) The model was designed for the purpose of experimental and

UNCLASSIFIED 7

DSTOndashTRndash2898 UNCLASSIFIED

1

2 345

6 7 8 91011

12 13 141516

17 181920

212223

24 252627

28 29 303132

33 34

35

Top view

Side view

Figure 5 Schematic of scale model showing static-pressure port locations green and redmarkers represent the starboard and port static-pressure ports respectively

numerical studies and has no full-scale equivalent While the full model includes a casingcentre fin and control surfaces all tests reported here were conducted on the axisymmetricbody shape only

The model was machined from aluminum and consists of an ellipsoidal nose a cylin-drical centre-body and a streamlined tail section At the design stage an N6 surface finishwas specified for the model which corresponds to a roughness of 08microm in waviness Af-ter manufacture the surface finish was checked using a Surface Roughness Indicator andthe finish was found to be better than the design specification The model was anodisedwhich increased the thickness of the natural oxide layer by about 10microm

The model is 1350 mm long with a maximum diameter of 185 mm and slendernessratio of 73 where the slenderness ratio is defined as hull length divided by maximumhull diameter The model contains 21 longitudinal static-pressure ports on the centre-lineof the upper surface and 14 lateral static-pressure ports offset to the port and starboardsides of the upper surface centre-line Figure 5 shows the stream-wise location of thestatic-pressure ports

The model was supported by a single pylon as shown in Figure 6 All tests were carriedout at zero angle of yaw and zero angle of pitch The origin of the body coordinate systemis located at the nose of the submarine model The x-axis corresponds to the axis ofsymmetry of the model

8 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 6 Submarine model mounted in LSWT showing pylon support and pitch controlarm

UNCLASSIFIED 9

DSTOndashTRndash2898 UNCLASSIFIED

Table 1 Details of tripping devices where the Reynolds number is based on the height ofthe device The minimum Reynolds number and maximum Reynolds number correspondto nominal freestream velocities of Uinfin = 40 ms and Uinfin = 70 ms respectively where his the height of the grit and w is the width of the grit

Device Dimensions (mm) RedT (min) RedT (max)

Wire 1 dT = 01 281 496Wire 2 dT = 02 577 1015Wire 3 dT = 05 1443 256680 Grit h = 021 w = 3 605 1073

33 Tripping Devices

In this work four tripping devices were tested and consisted of circular wires with diame-ters dT = 01 02 and 05 mm as well as a distributed silicon carbide grit of size 80 havinga width of 3 mm The circular wires were bent to conform to the local diameter of thesubmarine and then attached with ldquosuper-gluerdquo such that there was no gap between thewire and the model surface Figure 7 The silicon carbide grit is prepared by distributinga layer of grit on double-sided sticky tape the tape is then adhered to the submarineFigure 8 The tripping devices were attached to the submarine model circumferentiallylocated at a streamwise coordinate of x = 675 mm measured from the nose of the sub-marine which corresponds to 5 of the total model length The dimensions of the tripdevices along with the Reynolds number range of the trip devices are summarised inTable 1 Note that the Reynolds number of the trip device is defined as RedT = U1dT νwhere for the case of the 80 grit dT is replaced by the grit height h

34 Pressure Scanners

Pressure Systems Incorporated (PSI) brand pressure scanners were used to measure allstatic and total pressures The pressure scanners are differential pressure measurementunits consisting of an array of silicon piezoresistive pressure sensors one for each pressureport The outputs of the sensors are electronically multiplexed through a single on-boardinstrumentation amplifier using binary addressing The scanners include a two-positioncalibration manifold actuated by momentary pulses of control pressures In the calibrateposition all sensors are connected to a common calibration pressure port A series ofaccurately-measured pressures is applied through this port to characterize the sensorsProper and periodic on-line calibration maintains static errors within plusmn003 or betterof the full-scale pressure range

The pressure scanners are controlled and sampled using a PSI 8400 electronic measure-ment system It is a modular parallel processing system for high-speed pressure scanningat up to 20000 measurements per second and allows the use of digitally temperaturecompensated pressure scanners

Two differential pressure scanners were used in the experiments All pressures aremeasured relative to the free-stream static pressure pinfin as measured by the referencefree-stream Pitot-static probe Each pressure scanner contained 32 ports The full-scale

10 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 7 Location of trip wire

Figure 8 Photo showing the 3 mm wide band of 80 grit transition strip

UNCLASSIFIED 11

DSTOndashTRndash2898 UNCLASSIFIED

pressure range of the scanners is 249 kPa (ldquo10 inches-of-water scannerrdquo) and 689 kPa(ldquo1 psi scannerrdquo) The 689 kPa scanner was used to read the static pressure at the longi-tudinal ports as well as the output from the Preston tube and the Pitot-static probe

For the purpose of cross-checking and for redundancy the Preston tube was connectedto two independent ports of the 689 kPa scanner and the two readings averaged For thisscanner pressures could be read to an accuracy of 6890 times 00003 Pa ie about 2 Pa Theminimum ∆p measured by the Preston tube was 145 Pa which gives a pressure scannerresolution of 14 However this minimum ∆p was recorded for a location where thePreston tube was in a laminar boundary layer and such data is only useful in a qualitativesense (see Section 2) For locations were the boundary layer is turbulent the minimum ∆pwas 340 Pa which gives a pressure scanner resolution of 06 The 249 kPa scanner wasused mainly to acquire the static pressures at the lateral ports

35 Data Acquisition Software

A software package called ImPressOne was used which communicates with the PSI 8400and displays and acquires the pressure data for the model under test For the staticpressure measurements 100 readings were acquired at each pressure port at a samplingrate of 20 Hz For the Preston-tube measurements the sample rate was increased and100 samples were acquired at each pressure port at a sampling rate of 50 Hz for eachfree-stream velocity

36 Experimental Procedure

The hull was tested with each of the selected tripping devices listed in Table 1 as wellas without a tripping device resulting in five different test configurations For each testconfiguration the static pressures were initially acquired for that particular configurationfollowed by the Preston-tube measurements

A Preston tube having a diameter of 06 mm was attached to the surface of the modelusing both plasticine and tape to ensure that the tube was positioned as flat as possibleon the surface of the model as shown in Figure 9 Preston-tube measurement were takenon the upper surface of the submarine model along a line directly above the centre-lineof the model For the dT = 02 and 05 mm wires and the grit case measurements weretaken from x = 73 mm to x = 1065 mm for a total of 18 stations For the dT = 01 mmwire measurements were limited to 3 stations between x = 305 mm and x = 442 mmThe stream-wise coordinates for the Preston tube measurements are given in the Table 2Data were acquired for a range of free-stream velocities from 40 to 70 ms in incrementsof 5 ms

For each nominal velocity the corresponding model Reynolds number was calcu-lated assuming standard temperature and atmospheric pressure conditions 20C and101 325 Pa respectively For each given test the temperature and static pressure of theair within the test section were logged and the air density and viscosity were calculatedTo account for daily variations in temperature and atmospheric pressure the freestream

12 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Flow direction

Figure 9 Preston tube located on the centre-line of the upper-surface of submarine

velocity was adjusted to ensure that the model Reynolds number remained constant foreach given nominal velocity condition as shown in Table 3

Table 2 Skin-friction measurement stations Where applicable the corresponding staticport number is given For the dT = 01 mm wire measurements were only taken at stations3050 3600 as well as an additional station at x = 4425 mm

xmm 731 787 843 900 1125 1350 1575 1800 2150Static port - - - 6 - 7 - 8 -

xmm 2500 3050 3600 5250 7000 8700 9500 10100 10650Static port 9 - 12 13 14 17 18 21 24

Table 3 Reynolds numbers (based on submarine length 135 m) corresponding to thenominal free-stream velocities

Nominal Uinfin 40 45 50 55 60 65 70 msRe 358 403 448 493 537 582 627 times106

37 Data Reduction

The static pressure readings from the pressure ports were converted to pressure coefficientsusing the relationship

Cp =ps minus pinfinpt minus pinfin

(11)

where pinfin is the reference free-stream static pressure pt is the reference free-stream totalpressure and ps is the static pressure on the surface of the submarine model

As explained in Section 34 all Preston tube pressures are measured relative to the free-stream static pressure In order to apply the Preston tube calibration (4)-(6) the loggedPreston-tube pressure differences (ie pp minus pinfin) must first be converted to a ∆p = pp minus ps

UNCLASSIFIED 13

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

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Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

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Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

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43

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Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 19: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

Figure 4 LSWT Layout see Erm (2003)

3 Test Program

In this preliminary investigation four different tripping devices were used to investigatethe effect of the device on the skin-friction profile of a generic sub-scale submarine modelTests were conducted both with and without the tripping devices at a range of nominalfree-stream velocities Uinfin ranging from Uinfin = 40 to 70 ms to assess their effectivenessin tripping the boundary layer

31 Test Facility

The Low-Speed Wind Tunnel at DSTO is a closed circuit continuous flow tunnel with acontraction ratio of 41 The test section has an irregular octagonal shape with a heightof 213 m a width of 274 m and a length of 6553 m with a longitudinal turbulenceintensity of approximately 04 in the region where the models are tested (see Erm2003) An outline of the plan of the wind tunnel is shown in Figure 4 Free-streamvelocities were measured using static pressure rings at the upstream and downstreamends of the contraction A Pitot-static probe mounted on the side wall near the front ofthe working section was used to provide an independent measurement of the free-streamvelocity

32 Test Model

The sub-scale submarine model utilised in these tests is referred to as the Joubert modelsince the geometry is based on the work of Joubert (2004) and Joubert (2006) as well asLoid amp Bystrom (1983) The model was designed for the purpose of experimental and

UNCLASSIFIED 7

DSTOndashTRndash2898 UNCLASSIFIED

1

2 345

6 7 8 91011

12 13 141516

17 181920

212223

24 252627

28 29 303132

33 34

35

Top view

Side view

Figure 5 Schematic of scale model showing static-pressure port locations green and redmarkers represent the starboard and port static-pressure ports respectively

numerical studies and has no full-scale equivalent While the full model includes a casingcentre fin and control surfaces all tests reported here were conducted on the axisymmetricbody shape only

The model was machined from aluminum and consists of an ellipsoidal nose a cylin-drical centre-body and a streamlined tail section At the design stage an N6 surface finishwas specified for the model which corresponds to a roughness of 08microm in waviness Af-ter manufacture the surface finish was checked using a Surface Roughness Indicator andthe finish was found to be better than the design specification The model was anodisedwhich increased the thickness of the natural oxide layer by about 10microm

The model is 1350 mm long with a maximum diameter of 185 mm and slendernessratio of 73 where the slenderness ratio is defined as hull length divided by maximumhull diameter The model contains 21 longitudinal static-pressure ports on the centre-lineof the upper surface and 14 lateral static-pressure ports offset to the port and starboardsides of the upper surface centre-line Figure 5 shows the stream-wise location of thestatic-pressure ports

The model was supported by a single pylon as shown in Figure 6 All tests were carriedout at zero angle of yaw and zero angle of pitch The origin of the body coordinate systemis located at the nose of the submarine model The x-axis corresponds to the axis ofsymmetry of the model

8 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 6 Submarine model mounted in LSWT showing pylon support and pitch controlarm

UNCLASSIFIED 9

DSTOndashTRndash2898 UNCLASSIFIED

Table 1 Details of tripping devices where the Reynolds number is based on the height ofthe device The minimum Reynolds number and maximum Reynolds number correspondto nominal freestream velocities of Uinfin = 40 ms and Uinfin = 70 ms respectively where his the height of the grit and w is the width of the grit

Device Dimensions (mm) RedT (min) RedT (max)

Wire 1 dT = 01 281 496Wire 2 dT = 02 577 1015Wire 3 dT = 05 1443 256680 Grit h = 021 w = 3 605 1073

33 Tripping Devices

In this work four tripping devices were tested and consisted of circular wires with diame-ters dT = 01 02 and 05 mm as well as a distributed silicon carbide grit of size 80 havinga width of 3 mm The circular wires were bent to conform to the local diameter of thesubmarine and then attached with ldquosuper-gluerdquo such that there was no gap between thewire and the model surface Figure 7 The silicon carbide grit is prepared by distributinga layer of grit on double-sided sticky tape the tape is then adhered to the submarineFigure 8 The tripping devices were attached to the submarine model circumferentiallylocated at a streamwise coordinate of x = 675 mm measured from the nose of the sub-marine which corresponds to 5 of the total model length The dimensions of the tripdevices along with the Reynolds number range of the trip devices are summarised inTable 1 Note that the Reynolds number of the trip device is defined as RedT = U1dT νwhere for the case of the 80 grit dT is replaced by the grit height h

34 Pressure Scanners

Pressure Systems Incorporated (PSI) brand pressure scanners were used to measure allstatic and total pressures The pressure scanners are differential pressure measurementunits consisting of an array of silicon piezoresistive pressure sensors one for each pressureport The outputs of the sensors are electronically multiplexed through a single on-boardinstrumentation amplifier using binary addressing The scanners include a two-positioncalibration manifold actuated by momentary pulses of control pressures In the calibrateposition all sensors are connected to a common calibration pressure port A series ofaccurately-measured pressures is applied through this port to characterize the sensorsProper and periodic on-line calibration maintains static errors within plusmn003 or betterof the full-scale pressure range

The pressure scanners are controlled and sampled using a PSI 8400 electronic measure-ment system It is a modular parallel processing system for high-speed pressure scanningat up to 20000 measurements per second and allows the use of digitally temperaturecompensated pressure scanners

Two differential pressure scanners were used in the experiments All pressures aremeasured relative to the free-stream static pressure pinfin as measured by the referencefree-stream Pitot-static probe Each pressure scanner contained 32 ports The full-scale

10 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 7 Location of trip wire

Figure 8 Photo showing the 3 mm wide band of 80 grit transition strip

UNCLASSIFIED 11

DSTOndashTRndash2898 UNCLASSIFIED

pressure range of the scanners is 249 kPa (ldquo10 inches-of-water scannerrdquo) and 689 kPa(ldquo1 psi scannerrdquo) The 689 kPa scanner was used to read the static pressure at the longi-tudinal ports as well as the output from the Preston tube and the Pitot-static probe

For the purpose of cross-checking and for redundancy the Preston tube was connectedto two independent ports of the 689 kPa scanner and the two readings averaged For thisscanner pressures could be read to an accuracy of 6890 times 00003 Pa ie about 2 Pa Theminimum ∆p measured by the Preston tube was 145 Pa which gives a pressure scannerresolution of 14 However this minimum ∆p was recorded for a location where thePreston tube was in a laminar boundary layer and such data is only useful in a qualitativesense (see Section 2) For locations were the boundary layer is turbulent the minimum ∆pwas 340 Pa which gives a pressure scanner resolution of 06 The 249 kPa scanner wasused mainly to acquire the static pressures at the lateral ports

35 Data Acquisition Software

A software package called ImPressOne was used which communicates with the PSI 8400and displays and acquires the pressure data for the model under test For the staticpressure measurements 100 readings were acquired at each pressure port at a samplingrate of 20 Hz For the Preston-tube measurements the sample rate was increased and100 samples were acquired at each pressure port at a sampling rate of 50 Hz for eachfree-stream velocity

36 Experimental Procedure

The hull was tested with each of the selected tripping devices listed in Table 1 as wellas without a tripping device resulting in five different test configurations For each testconfiguration the static pressures were initially acquired for that particular configurationfollowed by the Preston-tube measurements

A Preston tube having a diameter of 06 mm was attached to the surface of the modelusing both plasticine and tape to ensure that the tube was positioned as flat as possibleon the surface of the model as shown in Figure 9 Preston-tube measurement were takenon the upper surface of the submarine model along a line directly above the centre-lineof the model For the dT = 02 and 05 mm wires and the grit case measurements weretaken from x = 73 mm to x = 1065 mm for a total of 18 stations For the dT = 01 mmwire measurements were limited to 3 stations between x = 305 mm and x = 442 mmThe stream-wise coordinates for the Preston tube measurements are given in the Table 2Data were acquired for a range of free-stream velocities from 40 to 70 ms in incrementsof 5 ms

For each nominal velocity the corresponding model Reynolds number was calcu-lated assuming standard temperature and atmospheric pressure conditions 20C and101 325 Pa respectively For each given test the temperature and static pressure of theair within the test section were logged and the air density and viscosity were calculatedTo account for daily variations in temperature and atmospheric pressure the freestream

12 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Flow direction

Figure 9 Preston tube located on the centre-line of the upper-surface of submarine

velocity was adjusted to ensure that the model Reynolds number remained constant foreach given nominal velocity condition as shown in Table 3

Table 2 Skin-friction measurement stations Where applicable the corresponding staticport number is given For the dT = 01 mm wire measurements were only taken at stations3050 3600 as well as an additional station at x = 4425 mm

xmm 731 787 843 900 1125 1350 1575 1800 2150Static port - - - 6 - 7 - 8 -

xmm 2500 3050 3600 5250 7000 8700 9500 10100 10650Static port 9 - 12 13 14 17 18 21 24

Table 3 Reynolds numbers (based on submarine length 135 m) corresponding to thenominal free-stream velocities

Nominal Uinfin 40 45 50 55 60 65 70 msRe 358 403 448 493 537 582 627 times106

37 Data Reduction

The static pressure readings from the pressure ports were converted to pressure coefficientsusing the relationship

Cp =ps minus pinfinpt minus pinfin

(11)

where pinfin is the reference free-stream static pressure pt is the reference free-stream totalpressure and ps is the static pressure on the surface of the submarine model

As explained in Section 34 all Preston tube pressures are measured relative to the free-stream static pressure In order to apply the Preston tube calibration (4)-(6) the loggedPreston-tube pressure differences (ie pp minus pinfin) must first be converted to a ∆p = pp minus ps

UNCLASSIFIED 13

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 20: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

1

2 345

6 7 8 91011

12 13 141516

17 181920

212223

24 252627

28 29 303132

33 34

35

Top view

Side view

Figure 5 Schematic of scale model showing static-pressure port locations green and redmarkers represent the starboard and port static-pressure ports respectively

numerical studies and has no full-scale equivalent While the full model includes a casingcentre fin and control surfaces all tests reported here were conducted on the axisymmetricbody shape only

The model was machined from aluminum and consists of an ellipsoidal nose a cylin-drical centre-body and a streamlined tail section At the design stage an N6 surface finishwas specified for the model which corresponds to a roughness of 08microm in waviness Af-ter manufacture the surface finish was checked using a Surface Roughness Indicator andthe finish was found to be better than the design specification The model was anodisedwhich increased the thickness of the natural oxide layer by about 10microm

The model is 1350 mm long with a maximum diameter of 185 mm and slendernessratio of 73 where the slenderness ratio is defined as hull length divided by maximumhull diameter The model contains 21 longitudinal static-pressure ports on the centre-lineof the upper surface and 14 lateral static-pressure ports offset to the port and starboardsides of the upper surface centre-line Figure 5 shows the stream-wise location of thestatic-pressure ports

The model was supported by a single pylon as shown in Figure 6 All tests were carriedout at zero angle of yaw and zero angle of pitch The origin of the body coordinate systemis located at the nose of the submarine model The x-axis corresponds to the axis ofsymmetry of the model

8 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 6 Submarine model mounted in LSWT showing pylon support and pitch controlarm

UNCLASSIFIED 9

DSTOndashTRndash2898 UNCLASSIFIED

Table 1 Details of tripping devices where the Reynolds number is based on the height ofthe device The minimum Reynolds number and maximum Reynolds number correspondto nominal freestream velocities of Uinfin = 40 ms and Uinfin = 70 ms respectively where his the height of the grit and w is the width of the grit

Device Dimensions (mm) RedT (min) RedT (max)

Wire 1 dT = 01 281 496Wire 2 dT = 02 577 1015Wire 3 dT = 05 1443 256680 Grit h = 021 w = 3 605 1073

33 Tripping Devices

In this work four tripping devices were tested and consisted of circular wires with diame-ters dT = 01 02 and 05 mm as well as a distributed silicon carbide grit of size 80 havinga width of 3 mm The circular wires were bent to conform to the local diameter of thesubmarine and then attached with ldquosuper-gluerdquo such that there was no gap between thewire and the model surface Figure 7 The silicon carbide grit is prepared by distributinga layer of grit on double-sided sticky tape the tape is then adhered to the submarineFigure 8 The tripping devices were attached to the submarine model circumferentiallylocated at a streamwise coordinate of x = 675 mm measured from the nose of the sub-marine which corresponds to 5 of the total model length The dimensions of the tripdevices along with the Reynolds number range of the trip devices are summarised inTable 1 Note that the Reynolds number of the trip device is defined as RedT = U1dT νwhere for the case of the 80 grit dT is replaced by the grit height h

34 Pressure Scanners

Pressure Systems Incorporated (PSI) brand pressure scanners were used to measure allstatic and total pressures The pressure scanners are differential pressure measurementunits consisting of an array of silicon piezoresistive pressure sensors one for each pressureport The outputs of the sensors are electronically multiplexed through a single on-boardinstrumentation amplifier using binary addressing The scanners include a two-positioncalibration manifold actuated by momentary pulses of control pressures In the calibrateposition all sensors are connected to a common calibration pressure port A series ofaccurately-measured pressures is applied through this port to characterize the sensorsProper and periodic on-line calibration maintains static errors within plusmn003 or betterof the full-scale pressure range

The pressure scanners are controlled and sampled using a PSI 8400 electronic measure-ment system It is a modular parallel processing system for high-speed pressure scanningat up to 20000 measurements per second and allows the use of digitally temperaturecompensated pressure scanners

Two differential pressure scanners were used in the experiments All pressures aremeasured relative to the free-stream static pressure pinfin as measured by the referencefree-stream Pitot-static probe Each pressure scanner contained 32 ports The full-scale

10 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 7 Location of trip wire

Figure 8 Photo showing the 3 mm wide band of 80 grit transition strip

UNCLASSIFIED 11

DSTOndashTRndash2898 UNCLASSIFIED

pressure range of the scanners is 249 kPa (ldquo10 inches-of-water scannerrdquo) and 689 kPa(ldquo1 psi scannerrdquo) The 689 kPa scanner was used to read the static pressure at the longi-tudinal ports as well as the output from the Preston tube and the Pitot-static probe

For the purpose of cross-checking and for redundancy the Preston tube was connectedto two independent ports of the 689 kPa scanner and the two readings averaged For thisscanner pressures could be read to an accuracy of 6890 times 00003 Pa ie about 2 Pa Theminimum ∆p measured by the Preston tube was 145 Pa which gives a pressure scannerresolution of 14 However this minimum ∆p was recorded for a location where thePreston tube was in a laminar boundary layer and such data is only useful in a qualitativesense (see Section 2) For locations were the boundary layer is turbulent the minimum ∆pwas 340 Pa which gives a pressure scanner resolution of 06 The 249 kPa scanner wasused mainly to acquire the static pressures at the lateral ports

35 Data Acquisition Software

A software package called ImPressOne was used which communicates with the PSI 8400and displays and acquires the pressure data for the model under test For the staticpressure measurements 100 readings were acquired at each pressure port at a samplingrate of 20 Hz For the Preston-tube measurements the sample rate was increased and100 samples were acquired at each pressure port at a sampling rate of 50 Hz for eachfree-stream velocity

36 Experimental Procedure

The hull was tested with each of the selected tripping devices listed in Table 1 as wellas without a tripping device resulting in five different test configurations For each testconfiguration the static pressures were initially acquired for that particular configurationfollowed by the Preston-tube measurements

A Preston tube having a diameter of 06 mm was attached to the surface of the modelusing both plasticine and tape to ensure that the tube was positioned as flat as possibleon the surface of the model as shown in Figure 9 Preston-tube measurement were takenon the upper surface of the submarine model along a line directly above the centre-lineof the model For the dT = 02 and 05 mm wires and the grit case measurements weretaken from x = 73 mm to x = 1065 mm for a total of 18 stations For the dT = 01 mmwire measurements were limited to 3 stations between x = 305 mm and x = 442 mmThe stream-wise coordinates for the Preston tube measurements are given in the Table 2Data were acquired for a range of free-stream velocities from 40 to 70 ms in incrementsof 5 ms

For each nominal velocity the corresponding model Reynolds number was calcu-lated assuming standard temperature and atmospheric pressure conditions 20C and101 325 Pa respectively For each given test the temperature and static pressure of theair within the test section were logged and the air density and viscosity were calculatedTo account for daily variations in temperature and atmospheric pressure the freestream

12 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Flow direction

Figure 9 Preston tube located on the centre-line of the upper-surface of submarine

velocity was adjusted to ensure that the model Reynolds number remained constant foreach given nominal velocity condition as shown in Table 3

Table 2 Skin-friction measurement stations Where applicable the corresponding staticport number is given For the dT = 01 mm wire measurements were only taken at stations3050 3600 as well as an additional station at x = 4425 mm

xmm 731 787 843 900 1125 1350 1575 1800 2150Static port - - - 6 - 7 - 8 -

xmm 2500 3050 3600 5250 7000 8700 9500 10100 10650Static port 9 - 12 13 14 17 18 21 24

Table 3 Reynolds numbers (based on submarine length 135 m) corresponding to thenominal free-stream velocities

Nominal Uinfin 40 45 50 55 60 65 70 msRe 358 403 448 493 537 582 627 times106

37 Data Reduction

The static pressure readings from the pressure ports were converted to pressure coefficientsusing the relationship

Cp =ps minus pinfinpt minus pinfin

(11)

where pinfin is the reference free-stream static pressure pt is the reference free-stream totalpressure and ps is the static pressure on the surface of the submarine model

As explained in Section 34 all Preston tube pressures are measured relative to the free-stream static pressure In order to apply the Preston tube calibration (4)-(6) the loggedPreston-tube pressure differences (ie pp minus pinfin) must first be converted to a ∆p = pp minus ps

UNCLASSIFIED 13

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 21: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

Figure 6 Submarine model mounted in LSWT showing pylon support and pitch controlarm

UNCLASSIFIED 9

DSTOndashTRndash2898 UNCLASSIFIED

Table 1 Details of tripping devices where the Reynolds number is based on the height ofthe device The minimum Reynolds number and maximum Reynolds number correspondto nominal freestream velocities of Uinfin = 40 ms and Uinfin = 70 ms respectively where his the height of the grit and w is the width of the grit

Device Dimensions (mm) RedT (min) RedT (max)

Wire 1 dT = 01 281 496Wire 2 dT = 02 577 1015Wire 3 dT = 05 1443 256680 Grit h = 021 w = 3 605 1073

33 Tripping Devices

In this work four tripping devices were tested and consisted of circular wires with diame-ters dT = 01 02 and 05 mm as well as a distributed silicon carbide grit of size 80 havinga width of 3 mm The circular wires were bent to conform to the local diameter of thesubmarine and then attached with ldquosuper-gluerdquo such that there was no gap between thewire and the model surface Figure 7 The silicon carbide grit is prepared by distributinga layer of grit on double-sided sticky tape the tape is then adhered to the submarineFigure 8 The tripping devices were attached to the submarine model circumferentiallylocated at a streamwise coordinate of x = 675 mm measured from the nose of the sub-marine which corresponds to 5 of the total model length The dimensions of the tripdevices along with the Reynolds number range of the trip devices are summarised inTable 1 Note that the Reynolds number of the trip device is defined as RedT = U1dT νwhere for the case of the 80 grit dT is replaced by the grit height h

34 Pressure Scanners

Pressure Systems Incorporated (PSI) brand pressure scanners were used to measure allstatic and total pressures The pressure scanners are differential pressure measurementunits consisting of an array of silicon piezoresistive pressure sensors one for each pressureport The outputs of the sensors are electronically multiplexed through a single on-boardinstrumentation amplifier using binary addressing The scanners include a two-positioncalibration manifold actuated by momentary pulses of control pressures In the calibrateposition all sensors are connected to a common calibration pressure port A series ofaccurately-measured pressures is applied through this port to characterize the sensorsProper and periodic on-line calibration maintains static errors within plusmn003 or betterof the full-scale pressure range

The pressure scanners are controlled and sampled using a PSI 8400 electronic measure-ment system It is a modular parallel processing system for high-speed pressure scanningat up to 20000 measurements per second and allows the use of digitally temperaturecompensated pressure scanners

Two differential pressure scanners were used in the experiments All pressures aremeasured relative to the free-stream static pressure pinfin as measured by the referencefree-stream Pitot-static probe Each pressure scanner contained 32 ports The full-scale

10 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 7 Location of trip wire

Figure 8 Photo showing the 3 mm wide band of 80 grit transition strip

UNCLASSIFIED 11

DSTOndashTRndash2898 UNCLASSIFIED

pressure range of the scanners is 249 kPa (ldquo10 inches-of-water scannerrdquo) and 689 kPa(ldquo1 psi scannerrdquo) The 689 kPa scanner was used to read the static pressure at the longi-tudinal ports as well as the output from the Preston tube and the Pitot-static probe

For the purpose of cross-checking and for redundancy the Preston tube was connectedto two independent ports of the 689 kPa scanner and the two readings averaged For thisscanner pressures could be read to an accuracy of 6890 times 00003 Pa ie about 2 Pa Theminimum ∆p measured by the Preston tube was 145 Pa which gives a pressure scannerresolution of 14 However this minimum ∆p was recorded for a location where thePreston tube was in a laminar boundary layer and such data is only useful in a qualitativesense (see Section 2) For locations were the boundary layer is turbulent the minimum ∆pwas 340 Pa which gives a pressure scanner resolution of 06 The 249 kPa scanner wasused mainly to acquire the static pressures at the lateral ports

35 Data Acquisition Software

A software package called ImPressOne was used which communicates with the PSI 8400and displays and acquires the pressure data for the model under test For the staticpressure measurements 100 readings were acquired at each pressure port at a samplingrate of 20 Hz For the Preston-tube measurements the sample rate was increased and100 samples were acquired at each pressure port at a sampling rate of 50 Hz for eachfree-stream velocity

36 Experimental Procedure

The hull was tested with each of the selected tripping devices listed in Table 1 as wellas without a tripping device resulting in five different test configurations For each testconfiguration the static pressures were initially acquired for that particular configurationfollowed by the Preston-tube measurements

A Preston tube having a diameter of 06 mm was attached to the surface of the modelusing both plasticine and tape to ensure that the tube was positioned as flat as possibleon the surface of the model as shown in Figure 9 Preston-tube measurement were takenon the upper surface of the submarine model along a line directly above the centre-lineof the model For the dT = 02 and 05 mm wires and the grit case measurements weretaken from x = 73 mm to x = 1065 mm for a total of 18 stations For the dT = 01 mmwire measurements were limited to 3 stations between x = 305 mm and x = 442 mmThe stream-wise coordinates for the Preston tube measurements are given in the Table 2Data were acquired for a range of free-stream velocities from 40 to 70 ms in incrementsof 5 ms

For each nominal velocity the corresponding model Reynolds number was calcu-lated assuming standard temperature and atmospheric pressure conditions 20C and101 325 Pa respectively For each given test the temperature and static pressure of theair within the test section were logged and the air density and viscosity were calculatedTo account for daily variations in temperature and atmospheric pressure the freestream

12 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Flow direction

Figure 9 Preston tube located on the centre-line of the upper-surface of submarine

velocity was adjusted to ensure that the model Reynolds number remained constant foreach given nominal velocity condition as shown in Table 3

Table 2 Skin-friction measurement stations Where applicable the corresponding staticport number is given For the dT = 01 mm wire measurements were only taken at stations3050 3600 as well as an additional station at x = 4425 mm

xmm 731 787 843 900 1125 1350 1575 1800 2150Static port - - - 6 - 7 - 8 -

xmm 2500 3050 3600 5250 7000 8700 9500 10100 10650Static port 9 - 12 13 14 17 18 21 24

Table 3 Reynolds numbers (based on submarine length 135 m) corresponding to thenominal free-stream velocities

Nominal Uinfin 40 45 50 55 60 65 70 msRe 358 403 448 493 537 582 627 times106

37 Data Reduction

The static pressure readings from the pressure ports were converted to pressure coefficientsusing the relationship

Cp =ps minus pinfinpt minus pinfin

(11)

where pinfin is the reference free-stream static pressure pt is the reference free-stream totalpressure and ps is the static pressure on the surface of the submarine model

As explained in Section 34 all Preston tube pressures are measured relative to the free-stream static pressure In order to apply the Preston tube calibration (4)-(6) the loggedPreston-tube pressure differences (ie pp minus pinfin) must first be converted to a ∆p = pp minus ps

UNCLASSIFIED 13

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 22: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

Table 1 Details of tripping devices where the Reynolds number is based on the height ofthe device The minimum Reynolds number and maximum Reynolds number correspondto nominal freestream velocities of Uinfin = 40 ms and Uinfin = 70 ms respectively where his the height of the grit and w is the width of the grit

Device Dimensions (mm) RedT (min) RedT (max)

Wire 1 dT = 01 281 496Wire 2 dT = 02 577 1015Wire 3 dT = 05 1443 256680 Grit h = 021 w = 3 605 1073

33 Tripping Devices

In this work four tripping devices were tested and consisted of circular wires with diame-ters dT = 01 02 and 05 mm as well as a distributed silicon carbide grit of size 80 havinga width of 3 mm The circular wires were bent to conform to the local diameter of thesubmarine and then attached with ldquosuper-gluerdquo such that there was no gap between thewire and the model surface Figure 7 The silicon carbide grit is prepared by distributinga layer of grit on double-sided sticky tape the tape is then adhered to the submarineFigure 8 The tripping devices were attached to the submarine model circumferentiallylocated at a streamwise coordinate of x = 675 mm measured from the nose of the sub-marine which corresponds to 5 of the total model length The dimensions of the tripdevices along with the Reynolds number range of the trip devices are summarised inTable 1 Note that the Reynolds number of the trip device is defined as RedT = U1dT νwhere for the case of the 80 grit dT is replaced by the grit height h

34 Pressure Scanners

Pressure Systems Incorporated (PSI) brand pressure scanners were used to measure allstatic and total pressures The pressure scanners are differential pressure measurementunits consisting of an array of silicon piezoresistive pressure sensors one for each pressureport The outputs of the sensors are electronically multiplexed through a single on-boardinstrumentation amplifier using binary addressing The scanners include a two-positioncalibration manifold actuated by momentary pulses of control pressures In the calibrateposition all sensors are connected to a common calibration pressure port A series ofaccurately-measured pressures is applied through this port to characterize the sensorsProper and periodic on-line calibration maintains static errors within plusmn003 or betterof the full-scale pressure range

The pressure scanners are controlled and sampled using a PSI 8400 electronic measure-ment system It is a modular parallel processing system for high-speed pressure scanningat up to 20000 measurements per second and allows the use of digitally temperaturecompensated pressure scanners

Two differential pressure scanners were used in the experiments All pressures aremeasured relative to the free-stream static pressure pinfin as measured by the referencefree-stream Pitot-static probe Each pressure scanner contained 32 ports The full-scale

10 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Figure 7 Location of trip wire

Figure 8 Photo showing the 3 mm wide band of 80 grit transition strip

UNCLASSIFIED 11

DSTOndashTRndash2898 UNCLASSIFIED

pressure range of the scanners is 249 kPa (ldquo10 inches-of-water scannerrdquo) and 689 kPa(ldquo1 psi scannerrdquo) The 689 kPa scanner was used to read the static pressure at the longi-tudinal ports as well as the output from the Preston tube and the Pitot-static probe

For the purpose of cross-checking and for redundancy the Preston tube was connectedto two independent ports of the 689 kPa scanner and the two readings averaged For thisscanner pressures could be read to an accuracy of 6890 times 00003 Pa ie about 2 Pa Theminimum ∆p measured by the Preston tube was 145 Pa which gives a pressure scannerresolution of 14 However this minimum ∆p was recorded for a location where thePreston tube was in a laminar boundary layer and such data is only useful in a qualitativesense (see Section 2) For locations were the boundary layer is turbulent the minimum ∆pwas 340 Pa which gives a pressure scanner resolution of 06 The 249 kPa scanner wasused mainly to acquire the static pressures at the lateral ports

35 Data Acquisition Software

A software package called ImPressOne was used which communicates with the PSI 8400and displays and acquires the pressure data for the model under test For the staticpressure measurements 100 readings were acquired at each pressure port at a samplingrate of 20 Hz For the Preston-tube measurements the sample rate was increased and100 samples were acquired at each pressure port at a sampling rate of 50 Hz for eachfree-stream velocity

36 Experimental Procedure

The hull was tested with each of the selected tripping devices listed in Table 1 as wellas without a tripping device resulting in five different test configurations For each testconfiguration the static pressures were initially acquired for that particular configurationfollowed by the Preston-tube measurements

A Preston tube having a diameter of 06 mm was attached to the surface of the modelusing both plasticine and tape to ensure that the tube was positioned as flat as possibleon the surface of the model as shown in Figure 9 Preston-tube measurement were takenon the upper surface of the submarine model along a line directly above the centre-lineof the model For the dT = 02 and 05 mm wires and the grit case measurements weretaken from x = 73 mm to x = 1065 mm for a total of 18 stations For the dT = 01 mmwire measurements were limited to 3 stations between x = 305 mm and x = 442 mmThe stream-wise coordinates for the Preston tube measurements are given in the Table 2Data were acquired for a range of free-stream velocities from 40 to 70 ms in incrementsof 5 ms

For each nominal velocity the corresponding model Reynolds number was calcu-lated assuming standard temperature and atmospheric pressure conditions 20C and101 325 Pa respectively For each given test the temperature and static pressure of theair within the test section were logged and the air density and viscosity were calculatedTo account for daily variations in temperature and atmospheric pressure the freestream

12 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Flow direction

Figure 9 Preston tube located on the centre-line of the upper-surface of submarine

velocity was adjusted to ensure that the model Reynolds number remained constant foreach given nominal velocity condition as shown in Table 3

Table 2 Skin-friction measurement stations Where applicable the corresponding staticport number is given For the dT = 01 mm wire measurements were only taken at stations3050 3600 as well as an additional station at x = 4425 mm

xmm 731 787 843 900 1125 1350 1575 1800 2150Static port - - - 6 - 7 - 8 -

xmm 2500 3050 3600 5250 7000 8700 9500 10100 10650Static port 9 - 12 13 14 17 18 21 24

Table 3 Reynolds numbers (based on submarine length 135 m) corresponding to thenominal free-stream velocities

Nominal Uinfin 40 45 50 55 60 65 70 msRe 358 403 448 493 537 582 627 times106

37 Data Reduction

The static pressure readings from the pressure ports were converted to pressure coefficientsusing the relationship

Cp =ps minus pinfinpt minus pinfin

(11)

where pinfin is the reference free-stream static pressure pt is the reference free-stream totalpressure and ps is the static pressure on the surface of the submarine model

As explained in Section 34 all Preston tube pressures are measured relative to the free-stream static pressure In order to apply the Preston tube calibration (4)-(6) the loggedPreston-tube pressure differences (ie pp minus pinfin) must first be converted to a ∆p = pp minus ps

UNCLASSIFIED 13

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

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Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

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IFIE

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UN

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ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

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Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

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IFIE

D

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ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

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Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

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UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 23: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

Figure 7 Location of trip wire

Figure 8 Photo showing the 3 mm wide band of 80 grit transition strip

UNCLASSIFIED 11

DSTOndashTRndash2898 UNCLASSIFIED

pressure range of the scanners is 249 kPa (ldquo10 inches-of-water scannerrdquo) and 689 kPa(ldquo1 psi scannerrdquo) The 689 kPa scanner was used to read the static pressure at the longi-tudinal ports as well as the output from the Preston tube and the Pitot-static probe

For the purpose of cross-checking and for redundancy the Preston tube was connectedto two independent ports of the 689 kPa scanner and the two readings averaged For thisscanner pressures could be read to an accuracy of 6890 times 00003 Pa ie about 2 Pa Theminimum ∆p measured by the Preston tube was 145 Pa which gives a pressure scannerresolution of 14 However this minimum ∆p was recorded for a location where thePreston tube was in a laminar boundary layer and such data is only useful in a qualitativesense (see Section 2) For locations were the boundary layer is turbulent the minimum ∆pwas 340 Pa which gives a pressure scanner resolution of 06 The 249 kPa scanner wasused mainly to acquire the static pressures at the lateral ports

35 Data Acquisition Software

A software package called ImPressOne was used which communicates with the PSI 8400and displays and acquires the pressure data for the model under test For the staticpressure measurements 100 readings were acquired at each pressure port at a samplingrate of 20 Hz For the Preston-tube measurements the sample rate was increased and100 samples were acquired at each pressure port at a sampling rate of 50 Hz for eachfree-stream velocity

36 Experimental Procedure

The hull was tested with each of the selected tripping devices listed in Table 1 as wellas without a tripping device resulting in five different test configurations For each testconfiguration the static pressures were initially acquired for that particular configurationfollowed by the Preston-tube measurements

A Preston tube having a diameter of 06 mm was attached to the surface of the modelusing both plasticine and tape to ensure that the tube was positioned as flat as possibleon the surface of the model as shown in Figure 9 Preston-tube measurement were takenon the upper surface of the submarine model along a line directly above the centre-lineof the model For the dT = 02 and 05 mm wires and the grit case measurements weretaken from x = 73 mm to x = 1065 mm for a total of 18 stations For the dT = 01 mmwire measurements were limited to 3 stations between x = 305 mm and x = 442 mmThe stream-wise coordinates for the Preston tube measurements are given in the Table 2Data were acquired for a range of free-stream velocities from 40 to 70 ms in incrementsof 5 ms

For each nominal velocity the corresponding model Reynolds number was calcu-lated assuming standard temperature and atmospheric pressure conditions 20C and101 325 Pa respectively For each given test the temperature and static pressure of theair within the test section were logged and the air density and viscosity were calculatedTo account for daily variations in temperature and atmospheric pressure the freestream

12 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Flow direction

Figure 9 Preston tube located on the centre-line of the upper-surface of submarine

velocity was adjusted to ensure that the model Reynolds number remained constant foreach given nominal velocity condition as shown in Table 3

Table 2 Skin-friction measurement stations Where applicable the corresponding staticport number is given For the dT = 01 mm wire measurements were only taken at stations3050 3600 as well as an additional station at x = 4425 mm

xmm 731 787 843 900 1125 1350 1575 1800 2150Static port - - - 6 - 7 - 8 -

xmm 2500 3050 3600 5250 7000 8700 9500 10100 10650Static port 9 - 12 13 14 17 18 21 24

Table 3 Reynolds numbers (based on submarine length 135 m) corresponding to thenominal free-stream velocities

Nominal Uinfin 40 45 50 55 60 65 70 msRe 358 403 448 493 537 582 627 times106

37 Data Reduction

The static pressure readings from the pressure ports were converted to pressure coefficientsusing the relationship

Cp =ps minus pinfinpt minus pinfin

(11)

where pinfin is the reference free-stream static pressure pt is the reference free-stream totalpressure and ps is the static pressure on the surface of the submarine model

As explained in Section 34 all Preston tube pressures are measured relative to the free-stream static pressure In order to apply the Preston tube calibration (4)-(6) the loggedPreston-tube pressure differences (ie pp minus pinfin) must first be converted to a ∆p = pp minus ps

UNCLASSIFIED 13

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

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Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

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Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

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Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

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SIF

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ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

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43

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Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 24: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

pressure range of the scanners is 249 kPa (ldquo10 inches-of-water scannerrdquo) and 689 kPa(ldquo1 psi scannerrdquo) The 689 kPa scanner was used to read the static pressure at the longi-tudinal ports as well as the output from the Preston tube and the Pitot-static probe

For the purpose of cross-checking and for redundancy the Preston tube was connectedto two independent ports of the 689 kPa scanner and the two readings averaged For thisscanner pressures could be read to an accuracy of 6890 times 00003 Pa ie about 2 Pa Theminimum ∆p measured by the Preston tube was 145 Pa which gives a pressure scannerresolution of 14 However this minimum ∆p was recorded for a location where thePreston tube was in a laminar boundary layer and such data is only useful in a qualitativesense (see Section 2) For locations were the boundary layer is turbulent the minimum ∆pwas 340 Pa which gives a pressure scanner resolution of 06 The 249 kPa scanner wasused mainly to acquire the static pressures at the lateral ports

35 Data Acquisition Software

A software package called ImPressOne was used which communicates with the PSI 8400and displays and acquires the pressure data for the model under test For the staticpressure measurements 100 readings were acquired at each pressure port at a samplingrate of 20 Hz For the Preston-tube measurements the sample rate was increased and100 samples were acquired at each pressure port at a sampling rate of 50 Hz for eachfree-stream velocity

36 Experimental Procedure

The hull was tested with each of the selected tripping devices listed in Table 1 as wellas without a tripping device resulting in five different test configurations For each testconfiguration the static pressures were initially acquired for that particular configurationfollowed by the Preston-tube measurements

A Preston tube having a diameter of 06 mm was attached to the surface of the modelusing both plasticine and tape to ensure that the tube was positioned as flat as possibleon the surface of the model as shown in Figure 9 Preston-tube measurement were takenon the upper surface of the submarine model along a line directly above the centre-lineof the model For the dT = 02 and 05 mm wires and the grit case measurements weretaken from x = 73 mm to x = 1065 mm for a total of 18 stations For the dT = 01 mmwire measurements were limited to 3 stations between x = 305 mm and x = 442 mmThe stream-wise coordinates for the Preston tube measurements are given in the Table 2Data were acquired for a range of free-stream velocities from 40 to 70 ms in incrementsof 5 ms

For each nominal velocity the corresponding model Reynolds number was calcu-lated assuming standard temperature and atmospheric pressure conditions 20C and101 325 Pa respectively For each given test the temperature and static pressure of theair within the test section were logged and the air density and viscosity were calculatedTo account for daily variations in temperature and atmospheric pressure the freestream

12 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Flow direction

Figure 9 Preston tube located on the centre-line of the upper-surface of submarine

velocity was adjusted to ensure that the model Reynolds number remained constant foreach given nominal velocity condition as shown in Table 3

Table 2 Skin-friction measurement stations Where applicable the corresponding staticport number is given For the dT = 01 mm wire measurements were only taken at stations3050 3600 as well as an additional station at x = 4425 mm

xmm 731 787 843 900 1125 1350 1575 1800 2150Static port - - - 6 - 7 - 8 -

xmm 2500 3050 3600 5250 7000 8700 9500 10100 10650Static port 9 - 12 13 14 17 18 21 24

Table 3 Reynolds numbers (based on submarine length 135 m) corresponding to thenominal free-stream velocities

Nominal Uinfin 40 45 50 55 60 65 70 msRe 358 403 448 493 537 582 627 times106

37 Data Reduction

The static pressure readings from the pressure ports were converted to pressure coefficientsusing the relationship

Cp =ps minus pinfinpt minus pinfin

(11)

where pinfin is the reference free-stream static pressure pt is the reference free-stream totalpressure and ps is the static pressure on the surface of the submarine model

As explained in Section 34 all Preston tube pressures are measured relative to the free-stream static pressure In order to apply the Preston tube calibration (4)-(6) the loggedPreston-tube pressure differences (ie pp minus pinfin) must first be converted to a ∆p = pp minus ps

UNCLASSIFIED 13

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 25: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

Flow direction

Figure 9 Preston tube located on the centre-line of the upper-surface of submarine

velocity was adjusted to ensure that the model Reynolds number remained constant foreach given nominal velocity condition as shown in Table 3

Table 2 Skin-friction measurement stations Where applicable the corresponding staticport number is given For the dT = 01 mm wire measurements were only taken at stations3050 3600 as well as an additional station at x = 4425 mm

xmm 731 787 843 900 1125 1350 1575 1800 2150Static port - - - 6 - 7 - 8 -

xmm 2500 3050 3600 5250 7000 8700 9500 10100 10650Static port 9 - 12 13 14 17 18 21 24

Table 3 Reynolds numbers (based on submarine length 135 m) corresponding to thenominal free-stream velocities

Nominal Uinfin 40 45 50 55 60 65 70 msRe 358 403 448 493 537 582 627 times106

37 Data Reduction

The static pressure readings from the pressure ports were converted to pressure coefficientsusing the relationship

Cp =ps minus pinfinpt minus pinfin

(11)

where pinfin is the reference free-stream static pressure pt is the reference free-stream totalpressure and ps is the static pressure on the surface of the submarine model

As explained in Section 34 all Preston tube pressures are measured relative to the free-stream static pressure In order to apply the Preston tube calibration (4)-(6) the loggedPreston-tube pressure differences (ie pp minus pinfin) must first be converted to a ∆p = pp minus ps

UNCLASSIFIED 13

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 26: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

pressure difference where pp is the Preston tube total pressure In order to convert thePreston pressure differences to ∆p values Cp data obtained without a Preston tube onthe surface are used The conversion is then given by

∆p = (pp minus pinfin)︸ ︷︷ ︸current

minus Cp︸︷︷︸prior

(pt minus pinfin)︸ ︷︷ ︸current

(12)

where ldquocurrentrdquo indicates data logged during the Preston-tube measurement and ldquopriorrdquoindicates data logged during the pressure-port measurements For stream-wise coordinateswhere there is no static pressure port the Cp data were interpolated using a cubic splineAn example of a cubic spline fit to the Cp data is given in Figure 10 for the case ofUinfin = 70 ms with the dT = 05 mm trip wire While the spline is a reasonable fitinspection of Figure 10 suggests a greater density of static pressure ports should be usedin future measurements

A C-language computer program was written to process the Preston-tube data anddetails of this program are given in Appendix B

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

U = 70ms dataSpline fit to data

Domain of Preston tube measurements

Figure 10 Example of a cubic spline fit to Cp data showing domain of Preston-tubedata Data is shown for the case of Uinfin = 70 ms with the dT = 05 mm trip wire

4 Results

41 Skin Friction Without a Tripping Device

Figure 11 shows the skin friction results as a function of stream-wise coordinate for thecase of no tripping device Care must be taken in interpreting the data for the no-tripping-

14 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

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35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

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IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 27: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

device case As explained in Section 2 a Preston tube can measure skin friction providedthe boundary layer is

1 in a fully turbulent state

2 the Preston tube is within the universal region of the boundary layer and

3 the strength of the pressure gradient does not effect the universal region of theboundary layer velocity profile

For the case of no tripping device the boundary layer is initially laminar and at somestream-wise coordinate natural transition occurs As a consequence the Cf values inferredby the Preston tube in the regions upstream of transition are incorrect owing to the factthat a universal turbulent region does not exist The data for these regions are marked bythe dashed curves in Figure 11 and quantitatively the data are of no use for the purposeof estimating the skin friction However qualitatively the data corresponding to laminarflow and transitioning flow can be used to estimate the point of transition which occursat the local minimum of the dashed curves in Figure 11

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 11 Skin friction development without tripping device Dashed lines indicate datawere obtained in a laminar or transitioning profile and in these regions the Preston tubemethod breaks down Only the data shown by the bold curves is quantitatively valid

To estimate the transition point a cubic function is fitted about the local minimumof the curves in Figure 11 The minimum of the cubic curve fit is then used to estimatethe transition point The estimates of the transition point are given in Table 4 for the

UNCLASSIFIED 15

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

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TO

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Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

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8U

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D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

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TO

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8U

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D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 28: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

range of free-stream velocities For the lowest measured velocity the transition point xtwas found to be about 340 mm from the nose of the submarine model As expected thetransition point moved upstream with increasing velocity and for the highest measuredvelocity the transition point was located at about 260 mm The trend of the transitionpoint with tunnel free-stream velocity indicates that transition is occurring ldquonaturallyrdquoand is not being initiated by any surface imperfections The local Reynolds numberbased on the stream-wise coordinate at transition varies between Rxt = 091 times 106 toRxt = 122 times 106 across the free-stream velocity range of the experiments It is possiblethat the Rxt variation is partially due to the error associated with estimating the transitionpoint using spatially sparse data and it is recommended that for future work measurementsare taken at more closely spaced streamwise stations in the transition region

Table 4 Estimate of transition point and transition Reynolds number based on Preston-tube results

Uinfin (ms) 40 45 50 55 60 65 70xt (mm) 343 330 291 306 302 295 263Rext (times106) 0910 0985 0966 112 120 127 122

42 Skin Friction With Tripping Devices

Skin friction coefficients over the submarine model for the case of trip wires with diametersof 02 mm and 05 mm as well as for 80 grit are given in Figures 12 13 and 14 respectivelyThese data as well as data for the case of no tripping device are given in Appendix Cwhere data are plotted for each test velocity

Figures 12 to 14 indicate that the shapes of the Cf profiles are similar for differentfree-stream velocities Increasing the free-stream velocity causes an overall shift of theprofile to lower values of Cf This is due to the associated increase in Reynolds numberthat occurs as free-stream velocity is increased (see section 422) For the case of a tripwire with dT = 05 mm and the 80 grit the location of the peak Cf does not progressupstream with increasing freestream velocity Interestingly for the case of a trip wirewith dT = 02 mm no local maximum in the Cf profile was resolved and the locationof the peak Cf is at the first measurement point downstream of the trip wire (ie 5 mmdownstream of the trip wire) Taking this point to represent the peak Cf it is evidentfrom Figure 12 that it also does not move upstream with increasing freestream velocityIt is concluded that wire tripping devices of diameter 02 and 05 mm as well as the grit80 tripping device are all effective in tripping the boundary layer at the lowest velocityused ie Uinfin = 40 ms as well as at higher velocities The data of these devices do notallow the lower limit of the trip Reynolds number to be established

A limited2 number of measurements where made with a 01 mm wire tripping deviceat stream-wise stations of 305 360 and 442 mm for the complete velocity range Figure 15shows the data for such a wire compared with data for the 02 and 05 mm wires as wellas data for the un-tripped case At the lowest freestream velocity the dT = 01 mm trip

2Ideally measurements at all the streamwise stations listed in Table 2 should have been made Howeverscheduling of the LSWT did not allow sufficient time for this to occur

16 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 29: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 12 Skin friction development using a dT = 02 mm trip wire

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 13 Skin friction development using a dT = 05 mm trip wire

UNCLASSIFIED 17

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 30: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

Uinfin = 40msminus1

45

50

55

60

65

70

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

Figure 14 Skin friction development using 80 grit roughness strip

wire did not force transition and the data are similar to those for the un-tripped case (asdiscussed in Section 41 values of Cf for laminar regions are not accurate) The Cf valuesfor the 45 ms case indicate the boundary layer is in a turbulent state for the dT = 01 mmwire However the higher values of Cf when compared to the larger diameter trips suggestthat transition is not occurring at the trip location but at some point downstream fromthe trip In this way the trip is acting to ldquoassistrdquo a natural transition rather than force itAs the free-stream velocity is increased values of Cf begin to reduce and the results forUinfin = 60 ms suggest that transition is occurring closer to the tripping device as for datashown in Figures 12 to 14 for the 02 and 05 wire tripping devices and the grit 80 device

The result for the dT = 01 mm wire at Uinfin = 60 ms establishes an absolute lowerbound on the trip device Reynolds number required to effectively trip the boundary layerThe trip device Reynolds number is defined using the velocity at the edge of the boundarylayer such that

RedT =U1dTν

=UinfindT

radic1 minus Cp

ν (13)

From the Cp results given in Section 43 it was found that at the location of the trip wireCp = minus007 also noting the actual freestream velocity was Uinfin = 62 ms for the nominalUinfin = 60 ms data yields a trip Reynolds number of RedT = 422 Given the lack of datacollected for the dT = 01 mm wire this value must be treated with caution as it cannot bedetermined whether the boundary layer remains under-stimulated in the region betweenthe tripping device (x = 675 mm) and the first measurement station (x = 3050 mm) Forthe dT = 02 mm wire the lowest value of the trip Reynolds number was RedT = 577 andas was shown above this was effective in causing transition Therefore it is recommendedthat RedT = 580 be taken as the lower limit for the trip device to cause effective transition

18 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

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TO

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8U

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IFIE

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Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

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IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

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LA

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D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 31: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

It is important to emphasise that the above finding is only applicable to the currentsubmarine model in the LSWT facility and with the trip device located at x = 675 mmThe size and type of device to use on the model in other facilities may be different andcould be influenced by many factors such as the quality of the flow in the tunnel

UNCLASSIFIED 19

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

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Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

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IFIE

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UN

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ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

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Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

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IFIE

D

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ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

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Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

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UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 32: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

No trip

d=01mm trip

d=02mm trip

d=05mm trip

Cf

Cf

times10minus3

times10minus3

x (mm)

x (mm)

Uinfin=40ms Uinfin=45ms Uinfin=50ms Uinfin=55ms

Uinfin=60ms Uinfin=65ms Uinfin=70ms

2

2

3

3

4

4

300300300

300300300300

400400400

400400400400

500500500

500500500500

Figure 15 Comparison of data for the dT = 01 mm trip wire and data for the larger tripwires and un-tripped case The Cf values for laminar regions are not accurate and suchdata are indicated with dashed lines - see Section 41

20U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

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IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 33: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

421 Comparison of the Different Trip Devices

The effect of the different tripping devices on the Cf development is shown in Figure 16for the case U = 40infinms Due to the lack of data the trip wire dT = 01 mm case isnot included in these comparisons As discussed above the effect of free-stream velocityon the tripped data is a bodily shift of the Cf profiles to lower values as Uinfin is increasedThe behaviour of the tripped results for the other free-stream velocities is similar to thatshown in Figure 16 However for completeness the equivalent plots for the higher free-stream velocities (Uinfin = 45 70 ms) are given in Appendix C

Based on Figure 16 and the accompanying plots in Appendix C all three trip devicescause a transition to a turbulent boundary layer For the stream-wise stations directlydownstream of the tripping device the local effect of the trip device is evident and allthree devices read differently in the region directly downstream of the tripping deviceThis is particularly the case for the dT = 05 mm trip wire which initially under readssignificantly compared with the other two trip devices The first data point on the curvefor the dT = 05 mm wire appears to be affected by the wake of the trip device and itis unlikely that the boundary layer profile at this location conforms to a universal wallprofile

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 16 Comparison of trip devices for Uinfin = 40 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer Model profileand trip location also shown

UNCLASSIFIED 21

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

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ndash289

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SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

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LA

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IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 34: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

sim Reminus15x solution

x = 525mm all trip devices

x = 700mm all trip devices

Cf

Rex

times10minus3

times1061

22

25

3

3

35

4

4

Figure 17 Comparison of Cf values with flat-plate zero-pressure-gradient solution Datafor stations x = 525 mm and x = 700 mm are plotted for all tripping devices

422 Scaling of Skin Friction with Reynolds Number

For a flat plate in a zero pressure gradient the turbulent boundary layer skin friction

coefficient approximately scales with Reminus15x (Schlichting 1978) where Rex is the Reynolds

number based on the stream-wise coordinate The Cf results for the submarine would beexpected to be influenced by longitudinal and lateral curvature However for the stream-wise coordinates where the pressure gradient is nominally zero the data are close to the

sim Reminus15x solution Figure 17 shows the x = 525 mm and x = 700 mm data for all the

tripping devices plotted as a function of Rex and there is a clear scaling with Rex

The Reminus15x scaling can be used to achieve reasonable collapse of the skin-friction data

across the velocity range of the experiments and this is shown in Figure 18 where the

product CfRe15x is plotted as a function of stream-wise coordinate This form of scaling

is useful in isolating the effects of the tripping device on the skin-friction profiles sinceit accounts for the Reynolds number variation as freestream velocity is varied Based onFigure 18 the three devices trip wires with diameters of 02 mm 05 mm and 80 grit allgive different readings in the region from the trip to station x = 360 mm Downstream ofstation x = 360 mm the data is considered to have collapsed to within experimental error

In order to further investigate the local effect of the different tripping devices Figure 18is replotted in an enlarged scale for the stations directly downstream of the tripping deviceFigure 19 For clarity only data corresponding to Uinfin le 50 ms is included in Figure 18and these data corresponds to a trip Reynolds number range 577 le RedT le 1807

22 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 35: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

The dT = 02 mm wire and 80 grit tripping devices give different readings directly aftof the tripping device but for stations x ge 1575 mm the results for these devices collapseFigure 19 The Reynolds numbers of these two trip devices are close (within 5 at agiven velocity) yet they produce different skin friction results for approximately 90 mmdownstream of the device and this length corresponds 450 trip heights This highlightsthat it is not just the Reynolds number (based on height) of the the device which affectsthe transition process but also the detailed geometry of the device

Curves for the dT = 05 mm trip wire exhibit a consistent difference from the curvesfor the other two devices in the region x lt 360 mm Figure 19 Regions of overshoot andundershoot are evident when compared with the other tripping devices and this behaviouris consistent across the velocity range of the experiments (see Appendix C) The initialunder reading then overshootundershoot behaviour of data for the 05 mm trip wiresuggests it is overstimulating the boundary layer

x (mm)

dT = 02mm all velocities

dT = 05mm all velocities

80 grit all velocities

CfRe15x

002

004

006

00 100 200 300 400 500 600 700 800 900 1000

locationTrip

Figure 18 Scaling skin friction data with Reynolds number Data for the complete rangeof velocities and trip devices are included Model profile and trip location also shown

423 Over-stimulation and the Maximum Trip Reynolds Number

Based on the analysis given in the preceding sections the trip wire of diameter dT =05 mm is deemed to have overstimulated the transition for all velocities tested Thelowest Reynolds number for this trip device occurs at Uinfin = 40 ms giving a value ofRedT = 1443 However analysis of the trip wire of diameter dT = 02 mm and 80 gritcases indicates that over-stimulation may also be occurring at trip Reynolds numbers lowerthan this value Figure 20 shows the skin-friction data for the dT = 02 mm and grit cases

plotted as the product CfRe15x versus x for the complete velocity range in the region

UNCLASSIFIED 23

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

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Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

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Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

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Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

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SIF

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ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

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43

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Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 36: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

dT = 02mm Uinfin le 50ms

dT = 05mm Uinfin le 50ms

80 grit Uinfin le 50ms

CfRe15x

005

006

007

100 150 200 250 300 350 400

Figure 19 Scaling skin friction data with Reynolds number For clarity only data forUinfin le 50 ms is included

directly aft of the tripping device For regions upstream of approximately 200 mm the datais scattered and shows no clear trends with Uinfin therefore attention is focused on the datafrom streamwise station x = 215 mm up to station x = 360 mm The station x = 215 mmcorresponds to approximately 700 trip heights downstream of the tripping device while

station x = 360 mm corresponds to the location where CfRe15x values collapse across the

complete Reynolds number range This region is shown as a dashed box in Figure 20 andit is clear that all but the two highest freestream velocity cases show good collapse in thisregion The trip Reynolds numbers at Uinfin = 60 ms are 865 and 913 for the dT = 02 mmwire and 80 grit cases respectively Based on these numbers it is recommended that thetrip Reynolds number not exceed RedT = 900

43 Pressure Coefficients

For the tripped boundary layer cases the pressure-coefficient data were found to collapsefor the complete range of free-stream velocities Figure 21 shows pressure coefficientsplotted as a function of stream-wise coordinate for the different tripping devices and theun-tripped case for a free-stream velocity of 70 ms It is apparent that the Cp data forthe case of no tripping device do not collapse indicating the boundary layer growth forthis case is different from the data obtained using tripping devices The lack of collapseis seen more clearly in the zoomed-in plot of Figure 22 This result is consistent with thedifferences noted in the Cf in Section 42

The Cp results of Figure 21 are almost identical at other free-stream velocities indi-cating that any change in boundary layer displacement thickness across the velocity range

24 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

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IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 37: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Uinfin=40ms

Uinfin=45ms

Uinfin=50ms

Uinfin=55ms

Uinfin=60ms

Uinfin=65ms

Uinfin=70ms

CfRe15x

CfRe15x

005

005

006

006

007

007

100 200 300 400

dT = 02mm

Grit

Overstimulated

Overstimulated

(a)

(b)

Figure 20 Comparison of scaled skin-friction for (a) dT = 02 mm and (b) 80 grit tripdevices Boxed region indicates region where assessment of data collapse has been made

UNCLASSIFIED 25

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 38: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Cp

minus02

02

04

06

08

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

locationTrip

Figure 21 Pressure coefficient measured at Uinfin = 70 ms Model profile and trip locationalso shown

tested has a negligible effect on Cp The quality of the collapse is illustrated in Figure 23where the data for the trip wire dT = 02 mm case is plotted for the range of free-streamvelocities The Cp data for the other trip devices and for the untripped case are plottedand tabulated in Appendix D

44 Pressure Gradients

As discussed in Section 2 sufficiently strong pressure gradients can modify the law-of-the-wall velocity profile (1) which would affect the accuracy of the Preston-tube calibrationcurves as given in (4)-(6) For such cases the non-dimensional pressure gradient parameterp+x enters the analysis (Nickels 2004) and (1) becomes

U

Uτ= f

(Uτy

ν p+x

) (14)

The parameter p+x would then be present in the forms of (4)-(6) and would need to becalibrated However provided p+x remains within the experimentally-determined limits ofthe Patel (1965) calibration the effect on the Preston-tube calibration is small Figure 24shows the pressure gradient parameter for the dT = 02 mm trip wire case and it is evidentthat the data is within the 3 error band of minus0005 lt p+x lt 001 as specified by (9a) and(10a)

26 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

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IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 39: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

x (mm)

Cp

minus02

minus01

01

0

0 200 400 600 800 1000 1200 1400

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure 22 Re-plot of Figure 21 with an expanded Cp axis showing more clearly thedifference between the tripped and un-tripped data

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure 23 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 02 mm case

UNCLASSIFIED 27

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 40: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

p+x =ν

ρU3τ

dp

dx

0002

0003

0001

minus0002

minus0003

minus0001 455055606570

0

0 100 200 300 400 500 600 700 800 900 1000

Figure 24 Non-dimensional pressure gradient across the range of free-stream velocitiesfor the trip wire dT = 02 mm case

28 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

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IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 41: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

5 Comparison with CFD Predictions

In parallel to the experimental program CFD methods are being developed for submarinegeometries The commercial CFD package Fluent has been benchmarked against existingexperimental and numerical results (for the ldquoDARPA SUBOFFrdquo model) to determineappropriate meshes and turbulence models to use Details of the CFD work are given inSnowden amp Widjaja (2011) Based on the findings of Snowden amp Widjaja further CFDpredictions have recently been performed for the Joubert submarine model (Snowdenprivate communication)

The CFD predictions applied to the Joubert submarine model (including the supportpylon and actuator arm) are shown in Figures 25 and 26 The CFD Cp results agree wellwith the current experimental results Figure 25 However the CFD Cf results are greaterthan the Cf data using tripping devices (eg data for dT = 02 mm Figure 26) The CFDmodel imposes a turbulent-boundary-layer solution from the nose of the model (x = 0)whereas the experimental results correspond to using tripping devices at x = 675 mm Thecurrent results demonstrate the sensitivity of the Cf evolution to the point of transition(compare the data for no trip device data with those using tripping devices) and thismay explain the difference between CFD and experimental data However further workis required to make firm conclusions regarding the differences in Figure 26 Perhaps CFDcould be applied to the case in which the boundary layer is laminar up to the trippingdevice and turbulent thereafter

experimental d = 02mm trip wire

x (mm)

Cp

CFD

minus04

minus02

02

04

06

08

0

0

1

200 400 600 800 1000 1200 1400

Figure 25 Comparison of experimental Cp measurements with CFD results for the Jou-bert submarine model Experimental data for dT = 02 mm wire for Uinfin = 60 ms

UNCLASSIFIED 29

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

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SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

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LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 42: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

experimental d = 02mm trip wire

Cf

times10minus3

x (mm)

CFD

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

Figure 26 Comparison of Preston tube skin-friction measurements with CFD results forthe Joubert submarine model Experimental data for dT = 02 mm wire with Uinfin = 60 ms

6 Conclusions

Use of the Preston-tube technique to measure turbulent skin friction coefficients along theupper surface of a generic submarine model in the LSWT was shown to be valid Turbulentskin-friction coefficients were measured for free-stream velocities varying from 40 ms to70 ms for the case of no tripping device for wires of diameter 01 02 and 05 mm andfor silicon carbide grit of size 80 The tripping devices were located 675 mm downstreamof the nose of the model which corresponds to 5 of its length

The wire of diameter 02 mm and the grit of size 80 where found to correctly stimulatetransition for freestream velocities varying from 40 ms to 60 ms For freestream veloc-ities higher than 60 ms both these devices appeared to be slightly overstimulating theboundary layer transition process The average height (h = 021 mm) of the grit elementswas only slightly more than the wire of diameter 02 mm However differences in the skinfriction values directly aft of these tripping devices were evident for approximately 450trip heights downstream of the respective devices From a model testing point of viewthese differences are considered to be negligible and of these two devices the wire is thepreferred option since it was observed that grit may erode during a testing program

The wire of diameter 05 mm was found to overstimulate the boundary layer transitionprocess for the complete velocity range of the experiments For the wire of diameter05 mm the effect of the over-stimulation was evident in the skin friction measurementsfor approximately 600 trip diameters downstream of the trip device Beyond this locationthe skin friction results for the wires of diameters 02 and 05 mm and for the grit were

30 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

UNCLASSIFIED 31

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

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TO

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8U

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IFIE

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Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

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IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

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LA

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D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 43: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

found to agree with each other

Only a limited range of streamwise data were collected for the trip wire of diameter01 mm However there were sufficient data to show that for freestream velocities less than60 ms that this device was under-stimulating the boundary layer transition The limiteddata for this case meant it was not possible to accurately determine the lowest velocityfor which this device correctly stimulated the transition

Based on the current results it is recommend that trip device be sized such thatthe Reynolds number of the trip device lies within the range 580 le RedT le 900 Thisensures that the boundary layer transition is correctly stimulated Under-stimulation ofthe boundary layer will generally have a more significant effect on the resulting skin-frictionvalues when compared to the case of over-stimulation where the effects are more subtleTherefore the upper bound of the above range can be relaxed slightly when carrying outtests over a range of freestream velocities and using a model with a fixed trip size

The above limits for RedT only apply in the LSWT for the Joubert model with atripping device located at 5 of the model length The findings cannot be directly appliedto other models tested in different tunnels due to possible differences in roughness of amodel pressure gradient about the nose of the model free-stream turbulence level noisegenerated by the tunnel wall boundary layers vibration of a model and flow irregularitiesin the free-stream

It was found that reasonable collapse of the skin-friction data across the velocity rangeof the experiments could be achieved if the skin friction data is multiplied by the localReynolds number to the power 15 ie the product CfRe

15 is a function of streamwisecoordinate alone

Whilst the Preston tube cannot be used to quantify the laminar skin friction it wasfound to provide a simple means of estimating the point of natural transition for thecases without a tripping device Without a tripping device natural transition of theboundary layer ranged between approximately x = 340 mm (at Uinfin = 40 ms) to 260 mm(at Uinfin = 70 ms) which corresponds to 25 and 19 of the model length respectivelyand Reynolds numbers of 091 times 106 and 122 times 106 respectively

Skin-friction coefficients measured on the submarine model in the LSWT were com-pared with CFD predictions for a limited number of tests Differences occurred betweenexperimental and predicted data possibly due to differences in the extent of turbulent flowover the model for the two cases For the experiments the flow was found to be turbulentdownstream of the tripping devices whereas for the CFD predictions a turbulent flowwas imposed over the entire length of the model

Pressure coefficients measured along the top surface of the submarine model were foundto show good agreement for the cases where a tripping device was used The measuredpressure coefficients showed good agreement with CFD predictions for the limited datacompared

Further work is required to quantify the boundary layer profile on the scale modelwhich would provide an improved means of assessing the effectiveness of the trip devicesused In addition the use of smaller trip devices could introduce errors into the measure-ments due to the difficulty in locating and attaching them on the surface of the modelAlternative tripping devices such as cylindrical pins need to be considered

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DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 44: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

7 Acknowledgements

The authors would like to acknowledge the following DSTO staff Alberto Gonzalez PaulJacquemin and John Clayton who provided support during the wind tunnel test programAdam Blandford who assisted in the use of the data acquisition software Bruce WoodyattHoward Quick and Ronny Widjaja who provided guidance and technical support andAndrew Snowden who provided preliminary CFD results for the Joubert submarine model

References

Braslow A L amp Knox E (1958) Simplified method for determination of critical heightof distributed roughness particles for boundary-layer transition at Mach numbers from0 to 5 Technical Note TN-4363 NASA

Coles D E (1956) The law of the wake in the turbulent boundary layer J Fluid Mech1 191ndash226

Coles D E (1962) The turbulent boundary layer in a compressible fluid TechnicalReport Rep R-403-PR The Rand Corporation Appendix A A manual of experimentalboundary-layer practice for low-speed flow

Erm L P (2003) Calibration of the flow in the extended test section of the low-speedwind tunnel at DSTO Tech Rep DSTO-TR-1384 Defence Science and TechnologyOrganisation Melbourne Australia

Erm L P amp Joubert P N (1991) Low-Reynolds-number turbulent boundary layers JFluid Mech 230 1ndash44

Fage A amp Preston J H (1941) On transition from laminar to turbulent flow in theboundary layer Proceedings of the Royal Society of London Series A Mathematicaland Physical Sciences 178(973) 201ndash227

Fernholz H H Janke G Schober M Wagner P M amp Warnack D (1996) Newdevelopments and applications of skin-friction measuring techniques Meas Sci Technol7 1396ndash1409

Gibbings J C (1959) Boundary layer transistion Prediction application to drag reduc-tion Technical Report CP-462 Aero Research Council

Gregory P (2006) Flow over a body of revolution in a steady turn PhD thesis Depart-ment of Mechanical and Manufacturing Engineering The University of Melbourne

Groves N C Huang T T amp Chang M S (1989) Geometric characteristics of darpasuboff models models (dtrc model nos 5470 and 5471) Technical Report DTRCSHD-1298-01 David Taylor Research Center Bethesda MD

Hosder S (2001) Unsteady Skin-Friction measurements on a Maneuvering Darpa2 SuboffModel Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute and StateUniversity

32 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

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IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 45: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

Jimenez J (2004) Turbulent flows over rough walls Ann Rev Fluid Mech 36 173ndash196

Jimenez J M Hultmark M amp Smits A J (2010a) The intermediate wake of a bodyof revolution at high Reynolds numbers J Fluid Mech 659 516ndash539

Jimenez J M Reynolds R T amp Smits A J (2010b) The effects of fins on theintermediate wake of a submarine model J Fluids Eng 132

Joubert P N (2004) Some aspects of submarine design part 1 hydrodynamics DSTO-TR 1622 DSTO

Joubert P N (2006) Some aspects of submarine design part 2 shape of a submarine2026 DSTO-TR 1920 DSTO

Loid H amp Bystrom L (1983) Hydrodynamic aspects of the design of the forward andaft bodies of the submarine In RINA International Symposium on Naval SubmarinesPaper No 19

Nickels T B (2004) Inner scaling for wall-bounded flows subject to large pressuregradients J Fluid Mech 521 217ndash239

Patel V (1965) Calibration of the Preston tube and limitations on its use in pressuregradients J Fluid Mech 23 185ndash205

Preston J (1954) The determination of turbulent skin friction by means of Pitot tubesJ Royal Aero Soc 58 109ndash121

Reed H amp Saric W (2008) Transition mechanisms for transport aircraft In 38th AIAAFluid Dynamics Conference and Exhibit

Schlatter P amp Henningson D S editors (2009) Proceedings of the Seventh IUTAMSymposium on Laminar-Turbulent Transition IUTAM Stockholm Sweden

Schlichting H (1978) Boundary Layer Theory McGraw-Hill Seventh Edition

Snowden A D amp Widjaja R (2011) CFD modelling of the DARPA SUBOFF submarinemodel in bare hull configuration Tech Rep DSTO-TR-2551 Defence Science andTechnology Organisation Melbourne Australia

Tani I Hama R amp Mituisi S (1940) On the permissible roughness in the laminarboundary layer Technical Report 199 Aero Res Inst Tokyo Imp Uni Also publishedas NASA-TM-89802

Tani I amp Sato H (1956) Boundary-layer transition by roughness element Journ PhysSoc Japan 12(12) 1284

Watt G D Nguyen V D Cooper K R amp Tanguay B (1993) Wind tunnel investi-gations of submarine hydrodynamics Canadian Aeronautics and Space Journal 39(3)119ndash126

Wetzel T G amp Simpson R L (1996) Unsteady flow over a 61 prolate spheroid Tech-nical Report VPI-AOE-232 Advanced Research Projects Agency through the Office ofNaval Research Applied Hydrodynamics Arlington VA USA

UNCLASSIFIED 33

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 46: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

White F M (1974) Viscous Fluid Flow McGraw-Hill New York

Whitfield C C (1999) Steady and unsteady force and moment data on a DARPA2submarine Masterrsquos thesis Aerospace Engineering Virginia Polytechnic Institute andState University

Zagarola M Williams D amp Smits A (2001) Calibration of the Preston probe for highReynolds number flows Measurement Science and Technology 12(4) 495ndash501

34 UNCLASSIFIED

UN

CL

AS

SIF

IED

DS

TO

ndashTR

ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

UN

CL

AS

SIF

IED

35

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

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Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

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Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

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Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

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SIF

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ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

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43

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Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

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Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

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DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

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DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 47: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

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ndash2898

Appendix A Summary of Tripping Devices Used in Previous Experiments

Table A1 Summary of tripping devices used in previous experiments Here d is the wireor pin diameter h is the pin height and s is the pin spacing

Researchers Model Air orWater

L (mm) D (mm) Trip Device(units mm)

Triplocation(mm)

Triplocation( of L)

Uinfin (ms) Re (times106)

Groveset al(1989)

SUBOFF Both 4356 508 Wire d = 0635 2159 496 not given not given

Groveset al(1989)

SUBOFF Air 4356 508 Wire d = 0635 2159 496 not given not given

Watt et al(1993)

Submarine Air 6000 Threedimensional

3 23

Wetzelamp Simpson(1996)

prolatespheroid

Air 1370 229 not given 274 20 45 42

Whitfield(1999)

DARPA2submarine

Air 2236 267 Cylindrical pinsh = 0762d = 127

3048 305 amp 427 42 amp 61

Hosder(2001)

DARPA2SUBOFF

Air 2240 Cylindrical pinsh = 076 d = 128s = 25

10 427 55

Gregory(2006)

Bodies ofrevolutionstraight andbent

Air 2580 260 Cylindrical pinsh = 0203 d = 0305s = 127

5 15 258

Jimenezetal(2010a)

SUBOFF Air 870 102 Wire d = 051 765 879 11 to 67

Jimenezetal(2010b)

SUBOFF Air 870 1016 Wire d = 10 254 292 049 amp 18

Unknown prolatespheroid

Air 1370 229 Cylindrical pinsh = 07 d = 12s = 25

20 507 to 552 42

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35

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Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 48: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

Appendix B Preston Tube Data Processing

A C-language computer program named PSI skin-frictionc was written to convertthe Preston-tube pressure measurements to skin-friction coefficients The program takesas input an experimental data file created by the ImPressOne data acquisition softwarea file containing the Cp distributions (for the given trip device) a file containing thefluid properties logged during the experiment (for the given trip device) and the locationof the Preston tube The output of the program PSI skin-frictionc contains theskin friction results at a given x coordinate for the range of freestream velocities testedFigure B1 summarises the input and output files Note for each trip device there is aseries of ImPressOne data files where each file corresponds to a unique location of thePreston tube The ImPressOne data file contains the averaged samples for all pressureports in blocks of data corresponding to the different freestream velocities

PSI skin-frictionc

(eg sfc port6 prestontxt)range of freestream velocitiesat a given location and for thefor a given tripping deviceFile containing skin friction data

Preston tube location

Fluid properties

experimental data fileImPressOne

for given trip device

Cp distribution

(eg sfc port6dat)

Figure B1 Input and output of program PSI skin-frictionc

Once all experimental data files have been processed the results can be collated into afile containing the skin friction coefficients as a function of x for a given trip device and fora given freestream velocity using the C-language computer program named merge datac

The source code for PSI skin-frictionc and merge datac are contained in thefollowing attachments which can be accessed by right-clicking on the icon

PSI skin-frictionc merge datac

Example input files for the program PSI skin-frictionc are provided in the follow-ing attachments The data files correspond to the experiment where a 05 mm trip wirewas used

sfc port6dat Cp trip-wire05txt fluid-propertiestxt

36 UNCLASSIFIED

extract preston tube data from PSI data file Compile with cc -Wall -o PSI_skin-friction PSI_skin-frictionc -lm -lgsl -lblas or to make a windowsXP version (requires GnuWin32 gsl dlls to be installed on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -LmntsambaGnuWin32lib -o PSI_skin-frictionexe PSI_skin-frictionc -lm -lgsl -lgslcblas or self-contained (no dlls require on client) i586-mingw32msvc-gcc -ImntsambaGnuWin32include -o PSI_skin-frictionexe PSI_skin-frictionc -lm mntsambaGnuWin32liblibgsla mntsambaGnuWin32liblibgslcblasa include ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgt gsl interpolation include ltgslgsl_splinehgtinclude ltgslgsl_interphgtinclude ltgslgsl_statistics_doublehgtdouble preston(doubledoubledouble)int tappings(int double )double spline(double double double int )int fluid_properties(doubledouble double int )int main() int Preston_chs[]=227228total_ch=226 define channels of interest double d=06 Preston tube diameter in mm double xtap[36] int ports[36] int ijkport_id[64][64]ncols[64]nrowsreceived=0DataSet int Preston_index[2][2]total_index[2] char fname[50]charloclinebuff[200]SearchFor[10]SemiColon[1]ans[]=y0 double pressure[64][64]p_dynU_infU_1p_preston[2]u_preston[2]Cp_localxlocal double nup_inftemprhoC_f[2]U_tau[2]psitopa=68947573 int ntaps=21 nvel=7velocities[]=40455055606570 double Cp[nvel][ntaps]Cp_xcoords[ntaps] double T[nvel]p_atm[nvel]Unomdelta_port int port_numberport_number_upport_number_down FILE finputfoutfCp while(ans[0]==y||ans[0]==Y) input data file printf(n Enter input data filet) scanf(sfname) finput=fopen(fnamer) find pressure tapping tappings(portsxtap) load Cp file and read all data fCp=fopen(Cp_trip-wire05txtr) fgets(linebuff200fCp) for(i=0iltntapsi++) i =gt x coordinate fscanf(fCplfampCp_xcoords[i]) for(j=0jltnvelj++) j =gt freestream velocity fscanf(fCplfampCp[j][i]) fclose(fCp) printf(Cp=8gnspline(200Cp_xcoordsCp[6]ntaps)) x coordinate printf( Is Preston tube at a pressure tappping ltyngtt) scanf(sans) if((ans[0]==y)||(ans[0]==Y)) printf( enter pressure tapping numbert) scanf(dampport_number) xlocal=xtap[port_number] else printf( enter pressure tapping number upstream of tubet) scanf(dampport_number_up) printf( enter pressure tapping number downstream of tubet) scanf(dampport_number_down) printf( enter the delta distance downstream of port d (ie 025 05)tport_number_up) scanf(lfampdelta_port) xlocal=xtap[port_number_up]+(xtap[port_number_down]-xtap[port_number_up])delta_port printf( x=8g (mm)nnxlocal) get fluid properties for each velocity fluid_properties(xlocalTp_atmnvel) for(i=0iltnveli++) printf(8g 8gnT[i]p_atm[i]) output data file charloc=strstr(fnamedat) charloc=0 strcat(fname_prestontxt) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave)n) fgets(linebuff200finput) while((charloc=strstr(linebuffPORT GROUP SCAN LISTS))==NULL) fgets(linebuff200finput) printf(snlinebuff) i=0 find the port ids while(strstr(linebuffTEST DATA)==NULL) fgets(linebuff200finput) charloc=amplinebuff[0] j=0 received=0 for()if(sscanf(charlocdampport_id[i][j])=1)break printf(d port_id[i][j]) if(port_id[i][j]==Preston_chs[0]) Preston_index[0][0]=i Preston_index[0][1]=jelse if(port_id[i][j]==Preston_chs[1]) Preston_index[1][0]=i Preston_index[1][1]=jelse if(port_id[i][j]==total_ch) total_index[0]=i total_index[1]=jif((charloc=strstr(charloc))==NULL)breakcharloc=charloc+1j=j+1received=1 if(received==1)ncols[i]=j printf(n) i=i+1 nrows=i printf(n) read data sets for() while((charloc=strstr(linebuffData Set))==NULL) if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break sscanf(linebuffdampDataSet) printf(Data Set dtDataSet) while((charloc=strstr(linebuffDescription))==NULL) if(fgets(linebuff200finput)==NULL)break Nominal velocity temperature and pressure if(fgets(linebuff200finput)==NULL)break sprintf(SearchFor_vel) charloc=strstr(linebuffSearchFor) sscanf(charloc+strlen(SearchFor)lfampUnom) for(k=0kltnvelk++)if(Unom==velocities[k])break temp=T[k] p_inf=p_atm[k] density and kinematic velocity rho=p_inf(287(temp+27315)) nu=1458E-06pow(temp+2731515)(temp+27315+1104)rho fprintf(foutd 8g 8g 8g 8g DataSetxlocalUnomtempp_inf1e3) while((charloc=strstr(linebuffTime))==NULL)if(fgets(linebuff200finput)==NULL)break if(fgets(linebuff200finput)==NULL)break PSI data for(i=0iltnrowsi++)for(j=0jltncols[i]j++) fscanf(finputlfcamppressure[i][j]SemiColon) Cp_local=spline(xlocalCp_xcoordsCp[k]ntaps) p_dyn=pressure[total_index[0]][total_index[1]]psitopa U_inf=sqrt(2p_dynrho) U_1=U_infsqrt(1-Cp_local) for(i=0ilt2i++) differance wrt freestream p_preston[i]=pressure[Preston_index[i][0]][Preston_index[i][1]]psitopa differance wrt local p_preston[i]=p_preston[i]-Cp_localp_dyn u_preston[i]=sqrt(2p_preston[i]rho) fprintf(fout8g 8g 8g 8g 8g 8g p_dynU_infp_preston[0]p_preston[1]u_preston[0]u_preston[1]) skin friction for(i=0ilt2i++)U_tau[i]=preston(u_preston[i]dnu)C_f[i]=2pow(U_tau[i]U_12) fprintf(fout8g 8g 8g 8g 8g 8gnU_tau[0]U_tau[1]C_f[0]C_f[1]U_1xlocal1e3nu(C_f[0]+C_f[1])2) printf(U_nominal=d (ms) Cp=8g Cf=8g Cf=8gnvelocities[k]Cp_localC_f[0]C_f[1]) fclose(finput) fclose(fout) printf(nData saved to file snProcess another file ltyngttfname) scanf(sans) return 0double preston(double udouble ddouble nu) calculate U_tau using Preston tube double xstarystarxdumdxdumystar_oldUtau xstar=log10(pow(u(d10000)nu20)80) if(xstarlt=2926) ystar=xstar2+0037 else if((xstargt2926)ampamp(xstarlt=5591)) ystar=08287-01381xstar+01437xstarxstar-06E-2xstarxstarxstar else if((xstargt5591)ampamp(xstarlt=7619)) ystar=40 ystar_old=00 while(fabs((ystar-ystar_old)ystar)gt1E-8) ystar_old=ystar xdum=ystar+20log10(0195E1ystar+041E1)-xstar dxdum=10+log(100)20195(0195E1ystar+041E1) ystar=ystar-xdumdxdum Utau=sqrt(pow(100ystar))20nu(d10000) return Utau spline fit to Cp data double spline(double xlocal double x double Cp int npts) gsl_interp_accel acc gsl_spline spline double c acc= gsl_interp_accel_alloc () spline= gsl_spline_alloc (gsl_interp_cspline npts) etsimate the value of Cp(xlocal) gsl_spline_init (spline x Cp npts) c=gsl_spline_eval (spline xlocal acc) gsl_spline_free (spline) gsl_interp_accel_free (acc) return cint tappings(int portsdouble xloc) ports[1]=201 ports[2]=202 ports[3]=203 ports[4]=204 ports[5]=205 ports[6]=206 ports[7]=207 ports[8]=208 ports[9]=209 ports[10]=210 ports[11]=211 ports[12]=212 ports[13]=213 ports[14]=214 ports[17]=215 ports[18]=216 ports[21]=217 ports[24]=218 ports[25]=219 ports[28]=220 ports[29]=221 ports[30]=222 ports[33]=223 ports[34]=224 ports[35]=225 ports[15]=101 ports[16]=102 ports[19]=103 ports[20]=104 ports[22]=105 ports[23]=106 ports[26]=107 ports[27]=108 ports[31]=109 ports[32]= 110 xloc[0]=674322 this is the trip location xloc[1]=0 xloc[2]=13978 xloc[3]=44974 xloc[4]=xloc[3] xloc[5]=xloc[3] xloc[6]=89974 xloc[7]=134974 xloc[8]=179974 xloc[9]=249974 xloc[10]=xloc[9] xloc[11]=xloc[9] xloc[12]=359974 xloc[13]=524974 xloc[14]=699974 xloc[15]=xloc[14] xloc[16]=xloc[14] xloc[17]=869974 xloc[18]=949974 xloc[19]=xloc[18] xloc[20]=xloc[18] xloc[21]=1009974 xloc[22]=xloc[21] xloc[23]=xloc[21] xloc[24]=1064974 xloc[25]=1099974 xloc[26]=xloc[25] xloc[27]=xloc[25] xloc[28]=1141974 xloc[29]=1174974 xloc[30]=1219974 xloc[31]=xloc[30] xloc[32]=xloc[30] xloc[33]=1256974 xloc[34]=1299974 xloc[35]=1348645 return 0 get fluid properties int fluid_properties(double xtargetdouble Tdouble p_atmint nvel) double x=0U int i char linebuff[200] FILE finput finput=fopen(fluid-propertiestxtr) fgets(linebuff200finput) header line while(fabs(1-xxtarget)gt1e-6) for(i=0iltnveli++) fgets(linebuff200finput) sscanf(linebufflflflflfampUampT[i]ampp_atm[i]ampx) fgets(linebuff200finput) blank line fclose(finput) return 0

C source code

cc -Wall -o merge_data merge_datac i586-mingw32msvc-gcc -o merge_dataexe merge_datacinclude ltstdlibhgtinclude ltstdiohgtinclude lterrnohgtinclude ltmathhgtinclude ltunistdhgtinclude ltstringhgtint main() int nbuf=500 char OS=U U for linux any other letter for Windows int i=0jnfilesnvel=7velocities[]=40455055606570 char fname[100]linebuff[nbuf] FILE finputfpreston[100]fout input data file printf( Enter list of input filest) scanf(sfname) finput=fopen(fnamer) while(fscanf(finputsfname)=EOF) fpreston[i]=fopen(fnamer) printf(opened file snfname) i=i+1 nfiles=i for(i=0iltnfilesi++) fgets(linebuffnbuffpreston[i]) header line for(j=0jltnvelj++) sprintf(fnameskin_friction_Udtxtvelocities[j]) fout=fopen(fnamew) fprintf(fout Data Set x (mm) Nominal velocity (ms) T (oC) p_inf (Pa) p_t-p_inf (Pa) Actual velocity (ms) p_preston-p_inf (Pa) Preston velocity (ms) U_tau (ms) Cf Rx Cf(ave) Cp dCpdx (m) p+ d+n) for(i=0iltnfilesi++)fgets(linebuffnbuffpreston[i])fprintf(foutslinebuff) fclose(fout) sort data - only on Unix on Windows_XP make sure the file list is ordered with streamwise coordinate if(OS==U)sprintf(linebuffsort -n --key=212 s gt tmptxtfname)system(linebuff)sprintf(linebuffmv tmptxt sfname)system(linebuff) printf(data saved to file snfname) for(i=0iltnfilesi++) fclose(fpreston[i]) fclose(finput) if(OS=U) printf(Return to exitn) getchar() getchar() return 0

C source code

ImPressOne Test Data File1313RUN NUMBER13621313DATE13250320111313START TIME13123201 PM1313TEST TITLE13SEA1000 Pressure Test - March 20111313TEST DESCRIPTION13SEA1000 Bare-Hull Model Model static ports amp Preston tube13No Balance1313131313DATA UNITS13psi1313DEFINED PRESSURE PORT GROUPS13SubTop13SubPort13SubStbd13Preston13ProbePt_Pt_Ps13ZER_S1S213VER_S1S21313PORT GROUP SCAN LISTS13 201 202 203 204 205 206 207 208 209 212 213 214 215 216 217 218 219 220 221 222 223 224 22513 201 204 210 101 103 105 107 109 22513 201 205 211 102 104 106 108 110 22513 227 22813 226 229 23013 132 23213 131 2311313TEST DATA1313Data Set13113Description13sfc_port6_vel4013Measurement Set13113Time13122207 PM13 014433403 005244281 -000179984 -000160627 -000654831 -001567278 -002741236 -002677661 -002341417 -000505304 -001806368 -000809105 -001389100 -002498103 -002622745 -002252189 -001743148 -001058478 -000414590 000561345 001300216 001793282 00151954513 014434782 -000158885 -002240678 -000994613 -002781495 -002671503 -001623884 000598254 00150500813 014440964 -000653480 -002247798 -001069037 -002805668 -002629421 -001509180 000655581 00149402513 008406086 00838567413 014713439 013672154 00020176013 -000002055 00000460213 000603626 0005860001313Data Set13213Description13sfc_port6_vel4513Measurement Set13113Time13122326 PM13 018410261 006690495 -000238364 -000201432 -000904225 -002003546 -003488644 -003417696 -002995673 -000612724 -002215789 -001032903 -001748912 -003182683 -003337758 -002856111 -002213450 -001338255 -000511337 000739644 001679801 002313675 00186602313 018392718 -000192541 -002851901 -001261330 -003557599 -003434391 -002079057 000805684 00188083113 018396103 -000897900 -002863118 -001352635 -003584156 -003353298 -001871783 000838995 00189563113 010756966 01073239413 018764974 017454351 00027188913 000000110 00000049913 000797252 0007791651313Data Set13313Description13sfc_port6_vel5013Measurement Set13113Time13122449 PM13 022667158 008250386 -000264312 -000235631 -001136923 -002448191 -004274214 -004190475 -003657710 -000770784 -002665443 -001246095 -002134163 -003899777 -004099652 -003498623 -002704788 -001612663 -000594989 000945133 002112716 002890838 00236006613 022669473 -000228844 -003490946 -001534049 -004353343 -004193386 -002529442 000963135 00235903613 022671607 -001121308 -003507039 -001648523 -004386777 -004112694 -002292378 001087486 00234858413 013252988 01322784013 023109627 021526763 00035325013 000001050 00000436613 001037537 0010267701313Data Set13413Description13sfc_port6_vel5513Measurement Set13113Time13122647 PM13 027760607 010132942 -000282212 -000236204 -001448028 -002948161 -005174628 -005099097 -004459890 -000865894 -003189932 -001491111 -002564775 -004742079 -004984732 -004224751 -003282530 -001944570 -000696269 001202699 002637101 003552002 00289413813 027778038 -000249179 -004226420 -001816685 -005322468 -005127122 -003067961 001276838 00290401513 027783185 -001431849 -004239002 -001971359 -005347265 -004998817 -002767984 001338852 00294051513 016103677 01607143613 028306285 026368243 00048719813 -000000203 00001104413 001392948 0013840781313Data Set13513Description13sfc_port6_vel6013Measurement Set13113Time13122817 PM13 033179793 012126899 -000318436 -000295791 -001813735 -003515428 -006181481 -006080403 -005323303 -001013701 -003757363 -001775831 -003061900 -005653394 -005936207 -005043253 -003907284 -002294101 -000803951 001486316 003205499 004255142 00340899213 033170989 -000300321 -005033256 -002161960 -006361181 -006116822 -003651409 001534857 00337860313 033171305 -001829170 -005058501 -002336893 -006381530 -005955878 -003270763 001625770 00339652713 019281445 01925634913 033857140 031521133 00061597913 000000523 00000210313 001749959 0017342301313Data Set13613Description13sfc_port6_vel6513Measurement Set13113Time13122944 PM13 039301020 014371581 -000362278 -000310155 -002215630 -004129092 -007290027 -007167035 -006273375 -001179794 -004394128 -002066460 -003585065 -006662557 -006996907 -005921254 -004597072 -002686593 -000907874 001799460 003848555 005052637 00393792213 039321062 -000293917 -005936423 -002467593 -007523569 -007218107 -004314209 001802200 00394749513 039326727 -002200846 -005960495 -002729581 -007539559 -007024068 -003816730 001957684 00395634813 022870024 02283955113 040014872 037364641 00079232013 -000001739 00000140613 002237091 0022236471313Data Set13713Description13sfc_port6_vel7013Measurement Set13113Time13123105 PM13 046125567 016861375 -000408021 -000340346 -002657904 -004817903 -008531471 -008397716 -007332998 -001346700 -005089233 -002385817 -004168595 -007786089 -008192702 -006912215 -005342419 -003092692 -000995892 002183821 004555472 005903419 00421737413 046135452 -000333183 -006895442 -002807653 -008863311 -008506260 -005002222 002218126 00421387713 046135604 -002693790 -006929666 -003168590 -008855667 -008249125 -004391560 002219733 00431779513 026701403 02666222813 047331530 043963948 00102290013 -000003835 00000950013 002791347 002771544131313ImPressOne Test Configuration Data1313TESTPLAN13CDocuments and SettingslswtMy DocumentsImPressOneTest Programssea-mar11Testplan FilesSEA1000 Pressure HS - 4xml1313PCU CONFIGURATION13PCU 1 crs 211 lrn 1 Pmax 1 psi13PCU 2 crs 215 lrn 5 Pmax 5 psi1313SDU CONFIGURATION13FIU crs 1121313SCANNER CONFIGURATION13Scanner 1 Type DTC 32 ports Pmax 036 lrn 113Scanner 2 Type DTC 32 ports Pmax 1 lrn 11313SETUP TABLE CONFIGURATION13Setup Table 100 frames 20000 usec 1 sets 2000 msec1313PRESSURE PORT GROUP CONFIGURATION13SubTop 23 port(s) 201-209212-22513SubPort 9 port(s) 20120421010110310510710922513SubStbd 9 port(s) 20120521110210410610811022513Preston 2 port(s) 22722813ProbePt_Pt_Ps 3 port(s) 22622923013ZER_S1S2 2 port(s) 13223213VER_S1S2 2 port(s) 131231131313

Experimental data

x (mm) Cp 40 Cp 45 Cp 50 Cp 55 Cp 60 Cp 65 Cp 700 098028538 098008349 098171955 098242551 098083516 098049783 0975730413978 035497405 035630864 035708256 035782083 035704783 035790515 03562833244974 -001437 -001262988 -001308555 -001220679 -001169418 -000989417 -00089325689974 -013842638 -013795538 -013888494 -013788235 -013770833 -013608797 -01340735134974 -018256289 -018328298 -018305795 -018219377 -018193383 -018011441 -017820774179974 -018160162 -018113187 -018126733 -017998025 -017909068 -017724174 -017500851249974 -015999053 -015913203 -015997359 -015873322 -015770887 -015626275 -015423148359974 -006577141 -006532929 -006506322 -006367483 -006230264 -006060737 -005931193524974 -004332241 -004277004 -004288066 -004153291 -004086651 -003924677 -003766752699974 -005550393 -005516436 -005559522 -005411503 -005359308 -005226872 -005050115869974 -009390736 -009341318 -009295492 -009190381 -009120348 -008979654 -008829535949974 -016898597 -016878289 -016923073 -016791064 -016736176 -016612894 -0164132391009974 -017626158 -0176184 -017675177 -017552156 -017466376 -017347247 -0171402361064974 -015103276 -015020087 -015006176 -014891326 -01480544 -014671927 -0144323791099974 -011648529 -011588364 -011600935 -011549244 -011449932 -011346793 -0111512031141974 -006984577 -006903898 -006831997 -006784555 -006639562 -00652726 -0063433981174974 -002527369 -002463995 -00245419 -002359488 -002231774 -002120289 -0019632441219974 004076499 004140013 004242509 004335877 004485303 004644098 0047123131256974 008913114 009049353 009217154 009266236 009418534 009564909 0095453071299974 012136927 012373695 012628446 012704886 012740091 012661726 0126247781348645 011531079 011323526 011409446 01111027 01121035 010852391 010463695

Cp distribution

U nominal ms Temperature deg C Atmos Press Pa location mm Location port U panel40 176 100940 89974 Port 6 45 177 100940 89974 Port 6 50 178 100940 89974 Port 6 55 182 100940 89974 Port 6 60 188 100940 89974 Port 6 65 192 100940 89974 Port 6 70 199 100940 89974 Port 6 40 176 100940 112474 Port 67 midpoint 45 177 100940 112474 Port 67 midpoint 50 178 100940 112474 Port 67 midpoint 55 182 100940 112474 Port 67 midpoint 60 188 100940 112474 Port 67 midpoint 65 192 100940 112474 Port 67 midpoint 70 199 100940 112474 Port 67 midpoint 40 198 100950 134974 Port 7 45 197 100950 134974 Port 7 50 198 100950 134974 Port 7 55 20 100950 134974 Port 7 60 204 100950 134974 Port 7 65 208 100950 134974 Port 7 70 214 100950 134974 Port 7 40 21 100950 157474 Port 78 midpoint 45 21 100950 157474 Port 78 midpoint 50 21 100950 157474 Port 78 midpoint 55 212 100950 157474 Port 78 midpoint 60 216 100950 157474 Port 78 midpoint 65 22 100950 157474 Port 78 midpoint 70 224 100950 157474 Port 78 midpoint 40 221 100950 179974 Port 8 45 22 100950 179974 Port 8 50 22 100950 179974 Port 8 55 222 100950 179974 Port 8 60 225 100950 179974 Port 8 65 229 100950 179974 Port 8 70 234 100950 179974 Port 8 40 231 100930 214974 Port 89 midpoint 45 23 100930 214974 Port 89 midpoint 50 23 100930 214974 Port 89 midpoint 55 232 100930 214974 Port 89 midpoint 60 234 100930 214974 Port 89 midpoint 65 238 100930 214974 Port 89 midpoint 70 241 100930 214974 Port 89 midpoint 40 237 100920 249974 Port 9 45 236 100920 249974 Port 9 50 235 100920 249974 Port 9 55 236 100920 249974 Port 9 60 239 100920 249974 Port 9 65 242 100920 249974 Port 9 70 247 100920 249974 Port 9 40 243 100910 304974 Port 912 midpoint 45 241 100910 304974 Port 912 midpoint 50 241 100910 304974 Port 912 midpoint 55 242 100910 304974 Port 912 midpoint 60 244 100910 304974 Port 912 midpoint 65 249 100910 304974 Port 912 midpoint 70 252 100910 304974 Port 912 midpoint 40 256 100910 359974 Port 12 45 254 100910 359974 Port 12 50 254 100910 359974 Port 12 55 254 100910 359974 Port 12 60 256 100910 359974 Port 12 65 259 100910 359974 Port 12 70 262 100910 359974 Port 12 40 261 100870 524974 Port 13 45 259 100870 524974 Port 13 50 258 100870 524974 Port 13 55 259 100870 524974 Port 13 60 262 100870 524974 Port 13 65 264 100870 524974 Port 13 70 268 100870 524974 Port 13 40 239 100600 7306765 1st stat aft trip 408945 239 100600 7306765 463650 24 100600 7306765 512655 245 100600 7306765 568760 249 100600 7306765 620865 253 100600 7306765 675770 261 100600 7306765 735 40 259 100600 787031 2nd stat aft trip 420345 256 100600 787031 465250 257 100600 787031 522655 259 100600 787031 575760 263 100600 787031 627365 267 100600 787031 682170 271 100600 787031 7326 40 269 100590 8433855 3rd stat aft trip 421245 265 100590 8433855 471150 265 100590 8433855 52455 267 100590 8433855 577860 271 100590 8433855 631865 276 100590 8433855 684370 28 100590 8433855 7367 40 20 100550 699974 Port 14 45 201 100550 699974 Port 14 50 202 100550 699974 Port 14 55 206 100550 699974 Port 14 60 21 100550 699974 Port 14 65 215 100550 699974 Port 14 70 223 100550 699974 Port 14 40 223 100550 869974 Port 17 45 223 100550 869974 Port 17 50 224 100550 869974 Port 17 55 228 100550 869974 Port 17 60 23 100550 869974 Port 17 65 233 100550 869974 Port 17 70 241 100550 869974 Port 17 40 239 100550 949974 Port 18 45 236 100550 949974 Port 18 50 237 100550 949974 Port 18 55 239 100550 949974 Port 18 60 242 100550 949974 Port 18 65 247 100550 949974 Port 18 70 251 100550 949974 Port 18 40 253 100550 1009974 Port 21 45 251 100550 1009974 Port 21 50 251 100550 1009974 Port 21 55 252 100550 1009974 Port 21 60 256 100550 1009974 Port 21 65 258 100550 1009974 Port 21 70 258 100550 1009974 Port 21 40 258 100550 1064974 Port 24 45 256 100550 1064974 Port 24 50 256 100550 1064974 Port 24 55 257 100550 1064974 Port 24 60 26 100550 1064974 Port 24 65 264 100550 1064974 Port 24 70 268 100550 1064974 Port 24

Fluid properties

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

CL

AS

SIF

IED

DS

TO

ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

43

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

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UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 49: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

Appendix C Skin Friction Coefficients

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C1 Comparison of trip devices for Uinfin = 45 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C2 Comparison of trip devices for Uinfin = 50 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

UNCLASSIFIED 37

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

DS

TO

ndashTR

ndash289

8U

NC

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IFIE

D

Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

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Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

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Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

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Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

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Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

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UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 50: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C3 Comparison of trip devices for Uinfin = 55 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C4 Comparison of trip devices for Uinfin = 60 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

38 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

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Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

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ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

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IED

41

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Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

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SS

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D

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ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

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43

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Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

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UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 51: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

Cf

times10minus3

x (mm)

01

2

3

4

5

6

7

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C5 Comparison of trip devices for Uinfin = 65 ms Dashed lines indicate data wereobtained in a laminar or transitioning boundary layer and in these regions the Preston tubemethod breaks down

Cf

times10minus3

x (mm)

01

2

3

4

5

6

100 200 300 400 500 600 700 800 900 1000

dT = 02mm trip wire

dT = 05mm trip wire

no trip

80 grit roughness

Figure C6 Comparison of trip devices for Uinfin = 70 ms For un-tripped data dashedcurve indicates a measurement in laminartransitioning boundary layer

UNCLASSIFIED 39

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Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

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ndashT

Rndash2898

Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

CL

AS

SIF

IED

41

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Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

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ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

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Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

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UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 52: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

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Table C1 Cf data for case of no trip device Bracketed values indicated a laminarboundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 (6388) 0234 (6476) 0262 (6714) 0287 (6738) 0313 (6715) 0340 (6693) 0369 (6634)7870 0225 (6131) 0254 (6304) 0283 (6533) 0313 (6567) 0341 (6572) 0371 (6554) 0403 (6482)8434 0244 (5993) 0275 (6158) 0305 (6419) 0337 (6437) 0369 (6471) 0400 (6468) 0433 (6418)8997 0263 (6000) 0296 (6129) 0328 (6375) 0362 (6392) 0395 (6393) 0431 (6389) 0466 (6352)11247 0332 (5314) 0375 (5517) 0415 (5853) 0459 (5931) 0501 (5982) 0545 (5982) 0591 (5970)13497 0401 (4520) 0449 (4740) 0500 (4940) 0552 (5204) 0605 (5308) 0656 (5377) 0707 (5416)15747 0467 (3939) 0527 (4112) 0586 (4300) 0645 (4589) 0704 (4691) 0765 (4776) 0831 (4832)17997 0535 (3532) 0601 (3684) 0667 (3852) 0737 (4023) 0806 (4242) 0868 (4338) 0948 (4401)21497 0637 (2959) 0715 (3121) 0795 (3290) 0877 (3451) 0958 (3690) 1041 (3788) 1128 (3864)24997 0733 (2402) 0828 (2565) 0917 (2704) 1012 (2851) 1108 (2994) 1203 (3197) 1303 (3284)30497 0874 (1579) 0988 (1674) 1092 (1756) 1209 (1904) 1319 (2213) 1432 (2856) 1545 (3496)35997 1016 (1360) 1143 (1886) 1263 (2853) 1392 (3759) 1524 (4158) 1652 (4083) 1788 (3931)44247 1231 4068 1381 3915 1537 3748 1692 3620 1846 3517 2006 3404 2155 338952497 1470 3775 1640 3672 1822 3525 2012 3409 2211 3288 2394 3196 2592 319669997 1964 3332 2203 3242 2449 3141 2712 3077 2952 3016 3207 2928 3471 294986997 2464 3198 2778 3137 3092 3024 3442 2971 3716 2922 4062 2878 4381 291294997 2813 3273 3135 3191 3496 3139 3850 3065 4208 3046 4586 2993 4965 2988100997 2998 3045 3352 2979 3758 2911 4163 2859 4499 2815 4902 2756 5298 2775106497 3104 2742 3492 2670 3903 2613 4293 2576 4685 2546 5088 2492 5495 2454

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

40U

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Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

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Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

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Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

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Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

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UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 53: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

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Table C2 Cf data for case of dT = 01 mm trip wire Bracketed values indicated alaminar boundary layer and values are provided for qualitative assessment only

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

30497 0872 (1636) 0982 3541 1093 3462 1203 3371 1313 3211 1426 3139 1541 314635997 1006 (2621) 1130 3363 1259 3256 1381 3140 1515 3016 1649 2951 1778 297444247 1222 3984 1375 3476 1533 3091 1693 3043 1837 2883 1996 2826 2162 2760

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

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Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

NC

LA

SS

IFIE

D

UN

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ndashT

Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

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Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

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UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 54: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

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Table C3 Cf data for case of dT = 02 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0207 6655 0233 6292 0259 6157 0285 5937 0311 5744 0339 5560 0363 54157870 0225 6542 0253 6171 0281 6052 0310 5845 0340 5670 0368 5523 0396 53768434 0243 5816 0272 5676 0303 5665 0336 5520 0359 5441 0399 5290 0432 51588997 0260 5748 0292 5676 0327 5580 0358 5431 0390 5295 0429 5173 0457 506511247 0331 4994 0372 4892 0413 4749 0455 4779 0497 4664 0542 4568 0580 446713497 0396 4714 0447 4499 0500 4390 0549 4433 0603 4326 0651 4241 0706 413415747 0464 4332 0524 4202 0581 4109 0641 4025 0707 4052 0759 3970 0821 387717997 0531 4143 0594 4007 0663 3907 0728 3829 0799 3868 0872 3771 0935 368621497 0631 3859 0713 3753 0793 3693 0866 3619 0950 3570 1031 3598 1111 351224997 0731 3695 0820 3608 0914 3522 1005 3451 1093 3395 1197 3415 1296 334430497 0873 3397 0979 3307 1092 3247 1204 3167 1318 3118 1426 3075 1538 308935997 1003 3184 1134 3113 1264 3047 1389 2989 1514 2931 1651 2890 1781 283252497 1453 3055 1631 2991 1822 2927 2002 2878 2189 2840 2388 2780 2556 274669997 1950 2915 2192 2874 2433 2821 2685 2773 2939 2728 3204 2688 3432 266786997 2457 2951 2777 2899 3083 2841 3403 2802 3708 2770 4033 2715 4371 267994997 2775 3098 3125 3052 3494 2970 3840 2920 4195 2908 4564 2857 4944 2888100997 2954 2879 3337 2792 3723 2756 4087 2708 4489 2668 4758 2650 5241 2585106497 3093 2574 3487 2530 3884 2484 4271 2431 4663 2408 5074 2379 5452 2342

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

42U

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Rndash2898

Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

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Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

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UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 55: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

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Table C4 Cf data for case of dT = 05 mm trip wire

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 1669 0232 2685 0257 3017 0285 3176 0311 3250 0339 3246 0369 32787870 0226 5268 0251 5102 0282 4967 0311 4970 0339 4803 0369 4636 0396 45128434 0243 5459 0273 5283 0304 5137 0336 5117 0367 4959 0396 4821 0429 46978997 0264 5307 0298 5182 0331 5081 0365 5065 0398 4954 0432 4859 0468 471111247 0331 5038 0372 4924 0414 4841 0455 4874 0499 4752 0541 4664 0586 456813497 0399 4827 0449 4709 0498 4630 0549 4657 0600 4570 0653 4476 0706 436715747 0463 4247 0522 4137 0581 4089 0641 4012 0699 4050 0760 3952 0824 387317997 0529 3906 0595 3827 0665 3757 0731 3688 0800 3730 0867 3664 0941 356821497 0632 3691 0712 3609 0791 3556 0870 3503 0953 3442 1023 3479 1128 337824997 0730 3571 0821 3495 0914 3408 1008 3360 1105 3304 1194 3355 1296 326030497 0872 3335 0978 3262 1092 3188 1210 3131 1324 3090 1429 3027 1564 303535997 1005 3138 1134 3068 1262 3022 1393 2942 1531 2885 1652 2841 1779 280452497 1456 3008 1633 2936 1824 2893 2011 2833 2192 2764 2382 2735 2576 271169997 1949 2925 2196 2858 2437 2816 2694 2763 2942 2725 3195 2702 3505 264586997 2472 2963 2777 2874 3084 2816 3404 2789 3740 2726 4047 2704 4383 266094997 2776 3089 3139 3038 3490 2977 3847 2913 4200 2902 4568 2862 4981 2870100997 2972 2865 3347 2780 3719 2750 4107 2705 4485 2655 4872 2634 5306 2650106497 3097 2604 3492 2538 3879 2502 4283 2458 4667 2430 5090 2383 5490 2345

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

UN

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Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 56: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DS

TO

ndashTR

ndash289

8U

NC

LA

SS

IFIE

D

Table C5 Cf data for case of 80 grit roughness strip

x (mm) Uinfin = 40 ms 45 50 55 60 65 70Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf Rex Cf

7307 0204 5036 0233 5306 0261 4859 0287 4932 0311 4893 0340 4811 0364 47577870 0226 5291 0252 5302 0280 5195 0310 5286 0338 5151 0368 4935 0398 48018434 0243 5373 0272 5294 0304 5189 0338 5193 0364 5075 0396 4881 0431 47998997 0260 5356 0293 5141 0326 5029 0357 5054 0392 4949 0427 4781 0463 463811247 0330 4953 0372 4791 0413 4723 0456 4737 0498 4625 0542 4519 0586 443113497 0398 4496 0449 4379 0497 4284 0548 4227 0599 4243 0651 4147 0706 404915747 0462 4287 0522 4155 0580 4085 0638 4013 0701 4048 0760 3965 0821 385917997 0531 4043 0594 3944 0665 3873 0733 3811 0799 3846 0866 3770 0938 367721497 0631 3853 0713 3769 0790 3677 0871 3608 0952 3550 1035 3572 1123 347824997 0729 3662 0819 3556 0912 3482 1006 3422 1098 3379 1196 3399 1293 331730497 0870 3399 0983 3320 1095 3242 1207 3166 1315 3123 1430 3081 1544 308135997 1008 3177 1132 3123 1262 3030 1393 2957 1518 2903 1651 2866 1780 279652497 1453 3051 1636 2948 1826 2887 2006 2836 2197 2793 2380 2734 2579 267269997 1951 2942 2201 2867 2441 2828 2686 2759 2943 2703 3193 2672 3461 261086997 2465 2942 2779 2858 3102 2812 3408 2769 3726 2726 4052 2703 4355 266594997 2774 3105 3133 2998 3486 2959 3841 2911 4204 2875 4566 2859 4941 2856100997 2960 2886 3336 2804 3717 2754 4094 2704 4479 2661 4878 2634 5261 2673106497 3104 2600 3494 2523 3893 2497 4271 2448 4680 2416 5088 2392 5470 2349

times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3 times106 times10minus3

44U

NC

LA

SS

IFIE

D

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 57: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

Appendix D Pressure Coefficients

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D1 Pressure coefficient across the range of free-stream velocities for the un-tripped case

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D2 Pressure coefficient across the range of free-stream velocities for the trip wiredT = 05 mm case

UNCLASSIFIED 45

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 58: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

x (mm)

Uinfin = 40msminus1

Cp

minus04

minus02

02

04

06

08

45

50

55

60

65

70

0

0

1

200 400 600 800 1000 1200 1400

Figure D3 Pressure coefficient across the range of free-stream velocities for the grit-80trip case

46 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 59: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

Table D1 Cp data for case of no trip device The table also gives the x coordinates of thestatic pressure ports where bracketed port numbers indicate the lateral ports which werenot connected

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Port No Cp Cp Cp Cp Cp Cp Cp

00 1 09779 09762 09767 09775 09768 09777 09740140 2 03520 03527 03538 03532 03537 03536 03530450 3 (4 5) -00190 -00186 -00185 -00193 -00187 -00179 -00173900 6 -01545 -01530 -01523 -01522 -01515 -01501 -014851350 7 -01940 -01927 -01918 -01908 -01902 -01886 -018671800 8 -01996 -01962 -01939 -01919 -01899 -01878 -018542500 9 (10 11) -01634 -01634 -01631 -01631 -01623 -01611 -016003600 12 -00834 -00764 -00690 -00618 -00605 -00598 -005925250 13 -00459 -00452 -00434 -00435 -00423 -00406 -003947000 14 (15 16) -00625 -00612 -00596 -00586 -00575 -00554 -005418700 17 -00963 -00954 -00945 -00937 -00926 -00915 -009039500 18 (19 20) -01717 -01709 -01704 -01706 -01697 -01684 -0167010100 21 (22 23) -01910 -01882 -01865 -01849 -01833 -01814 -0179210650 24 -01547 -01534 -01528 -01523 -01513 -01501 -0148611000 25 (26 27) -01330 -01302 -01275 -01259 -01238 -01214 -0119511420 28 -00913 -00878 -00840 -00808 -00785 -00755 -0073111750 29 -00375 -00351 -00330 -00307 -00295 -00274 -0025212200 30 (31 32) 00283 00303 00342 00366 00390 00407 0042912570 33 00856 00864 00890 00913 00932 00945 0095813000 34 01209 01239 01265 01276 01284 01276 0126513486 35 00842 00939 00958 00969 00970 00984 00991

UNCLASSIFIED 47

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 60: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

Table D2 Cp data for case of dT = 02 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

0 09799 09796 09814 09812 09812 09789 09741140 03572 03561 03579 03590 03595 03568 03573450 -00145 -00138 -00127 -00111 -00105 -00111 -00087900 -01419 -01385 -01375 -01364 -01359 -01354 -013281350 -01802 -01802 -01796 -01782 -01777 -01768 -017391800 -01777 -01771 -01764 -01748 -01740 -01729 -017062500 -01571 -01564 -01555 -01541 -01532 -01520 -014993600 -00625 -00623 -00606 -00594 -00582 -00572 -005525250 -00412 -00402 -00389 -00379 -00370 -00356 -003417000 -00523 -00520 -00511 -00499 -00492 -00479 -004658700 -00913 -00908 -00892 -00880 -00871 -00858 -008429500 -01656 -01650 -01648 -01632 -01627 -01614 -0159610100 -01751 -01746 -01736 -01723 -01712 -01699 -0168010650 -01494 -01487 -01472 -01457 -01445 -01431 -0141211000 -01138 -01134 -01126 -01112 -01101 -01092 -0107711420 -00682 -00672 -00663 -00646 -00635 -00623 -0060911750 -00223 -00220 -00212 -00198 -00189 -00181 -0016912200 00431 00442 00445 00467 00474 00484 0049512570 00917 00928 00932 00951 00957 00972 0098413000 01210 01239 01257 01264 01272 01277 0129513486 01089 01130 01149 01152 01139 01122 01102

48 UNCLASSIFIED

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 61: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

UNCLASSIFIED DSTOndashTRndash2898

Table D3 Cp data for case of dT = 05 mm trip wire

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09803 09801 09817 09824 09808 09805 09757140 03550 03563 03571 03578 03570 03579 03563450 -00144 -00126 -00131 -00122 -00117 -00099 -00089900 -01384 -01380 -01389 -01379 -01377 -01361 -013411350 -01826 -01833 -01831 -01822 -01819 -01801 -017821800 -01816 -01811 -01813 -01800 -01791 -01772 -017502500 -01600 -01591 -01600 -01587 -01577 -01563 -015423600 -00658 -00653 -00651 -00637 -00623 -00606 -005935250 -00433 -00428 -00429 -00415 -00409 -00392 -003777000 -00555 -00552 -00556 -00541 -00536 -00523 -005058700 -00939 -00934 -00930 -00919 -00912 -00898 -008839500 -01690 -01688 -01692 -01679 -01674 -01661 -0164110100 -01763 -01762 -01768 -01755 -01747 -01735 -0171410650 -01510 -01502 -01501 -01489 -01481 -01467 -0144311000 -01165 -01159 -01160 -01155 -01145 -01135 -0111511420 -00698 -00690 -00683 -00678 -00664 -00653 -0063411750 -00253 -00246 -00245 -00236 -00223 -00212 -0019612200 00408 00414 00424 00434 00449 00464 0047112570 00891 00905 00922 00927 00942 00956 0095513000 01214 01237 01263 01270 01274 01266 0126213486 01153 01132 01141 01111 01121 01085 01046

UNCLASSIFIED 49

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 62: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

DSTOndashTRndash2898 UNCLASSIFIED

Table D4 Cp data for case of grit-80

Uinfin = 40 ms 45 50 55 60 65 70x (mm) Cp Cp Cp Cp Cp Cp Cp

00 09794 09815 09798 09820 09815 09815 09750140 03553 03562 03571 03584 03583 03583 03559450 -00117 -00094 -00075 -00052 -00048 -00048 -00021900 -01402 -01391 -01371 -01357 -01349 -01349 -013151350 -01818 -01812 -01800 -01787 -01781 -01781 -017471800 -01780 -01764 -01759 -01741 -01735 -01735 -017012500 -01577 -01573 -01561 -01545 -01545 -01545 -015073600 -00637 -00627 -00618 -00597 -00593 -00593 -005675250 -00419 -00401 -00399 -00381 -00376 -00376 -003497000 -00545 -00533 -00526 -00507 -00500 -00500 -004778700 -00934 -00914 -00911 -00893 -00884 -00884 -008589500 -01668 -01652 -01655 -01639 -01633 -01633 -0160410100 -01772 -01754 -01750 -01734 -01722 -01722 -0169210650 -01507 -01487 -01482 -01463 -01450 -01450 -0142011000 -01161 -01149 -01142 -01127 -01120 -01120 -0109411420 -00688 -00671 -00670 -00651 -00641 -00641 -0061911750 -00251 -00234 -00223 -00208 -00198 -00198 -0018012200 00403 00415 00433 00454 00461 00461 0047912570 00878 00902 00916 00942 00948 00948 0096313000 01191 01220 01227 01260 01257 01257 0127213486 00972 01049 01042 01062 01056 01056 01023

50 UNCLASSIFIED

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA
Page 63: Skin-friction Measurements on a Model Submarine · Skin-Friction Measurements on a Model Submarine M. B. Jones, L. P. Erm, A. Valiy and S. M. Henbest Aerospace Division Defence Science

Page classification UNCLASSIFIED

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA

1 CAVEATPRIVACY MARKING

2 TITLE

Skin-Friction Measurements on a Model Subma-rine

3 SECURITY CLASSIFICATION

Document (U)Title (U)Abstract (U)

4 AUTHORS

M B Jones L P Erm A Valiyff and S MHenbest

5 CORPORATE AUTHOR

Defence Science and Technology Organisation506 Lorimer StFishermans Bend Victoria 3207 Australia

6a DSTO NUMBER

DSTOndashTRndash28986b AR NUMBER

AR 015-7446c TYPE OF REPORT

Technical Report7 DOCUMENT DATE

October 2013

8 FILE NUMBER 9 TASK NUMBER

ERP0729910 TASK SPONSOR

CDS11 No OF PAGES

4612 No OF REFS

0

13 URL OF ELECTRONIC VERSION

httpwwwdstodefencegovau

publicationsscientificphp

14 RELEASE AUTHORITY

Chief Aerospace Division

15 SECONDARY RELEASE STATEMENT OF THIS DOCUMENT

Approved for Public Release

OVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE PO BOX 1500EDINBURGH SOUTH AUSTRALIA 5111

16 DELIBERATE ANNOUNCEMENT

No Limitations

17 CITATION IN OTHER DOCUMENTS

No Limitations

18 DSTO RESEARCH LIBRARY THESAURUS

SubmarinesSkin frictionTurbulent boundary layerModellingFluid dynamics

19 ABSTRACT

Experimental skin-friction and pressure-coefficient data for a generic scale-model submarine testedin the Low-Speed Wind Tunnel at DSTO are presented The effect on skin-friction and pressurecoefficients due to different sizes and types of boundary layer tripping devices including the case of notripping device was investigated for the Reynolds number range of 358times 106 to 627times 106 where theReynolds number is based on model length Skin friction was measured using the Preston-tube methodwhich is a technique applicable to turbulent boundary layers only For the laminar and transitionregions the Preston tube only provided qualitative results The results demonstrate the importance ofcorrectly tripping the boundary layer and provide a guide on determining the size and type of trippingdevice required to achieve a correctly stimulated turbulent boundary layer for a given tunnel free-streamvelocity While the results are specific to the model geometry tested and for the given trip locationthe methodology is applicable to other general model geometries and trip locations This report doesnot address the difficult problem of where to place the trip

Page classification UNCLASSIFIED

  • ABSTRACT
  • Executive Summary
  • Authors
  • Contents
  • Glossary
  • Notation
  • Introduction
    • Boundary-Layer Transition
    • Approach of Erm amp Joubert (1991)
    • Empirical Expressions to Determine Sizes of Tripping Devices
      • Preston-Tube Method of Measuring Skin-Friction Coefficients
      • Test Program
        • Test Facility
        • Test Model
        • Tripping Devices
        • Pressure Scanners
        • Data Acquisition Software
        • Experimental Procedure
        • Data Reduction
          • Results
            • Skin Friction Without a Tripping Device
            • Skin Friction With Tripping Devices
              • Comparison of the Different Trip Devices
              • Scaling of Skin Friction with Reynolds Number
              • Over-stimulation and the Maximum Trip Reynolds Number
                • Pressure Coefficients
                • Pressure Gradients
                  • Comparison with CFD Predictions
                  • Conclusions
                  • Acknowledgements
                  • Summary of Tripping Devices Used in Previous Experiments
                  • Preston Tube Data Processing
                  • Skin Friction Coefficients
                  • Pressure Coefficients
                  • DISTRIBUTION LIST
                  • DOCUMENT CONTROL DATA