supplemental calibration of the aedc-pwt 16-ft ... - dtic

i I

B I=

AEDC-TR-80-32

Supplemental Calibration of the AEDC-PWT 6-ft Transonic Tunnel Aerodynamic Test Section

M. L. Mills ARO, Inc.

.=

July 1981

Final Report for Period December 1979 - June 1980

Approved for public release; distribution unlimited.

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AIR FORCE STATION, TENNESSEE

AIR FORCE SYSTEMS COMMAND UNITED STATES AIR FORCE

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i

APPROVAL STATEMENT

This report has been reviewed and approved.

ALEXANDER F. MONEY Directorate of Technology Deputy for Operations

Approved for publication:'

FOR THE COMMANDER

JOHN M. RAMPY Director of

Aerospace Flight Dynamics Test Deputy for Operations

UNCLASSIFIED R E P O R T D O C U M E N T A T I O N P A G E

I R E P O R T N U M B E R 12 G O V T A C C E S S I O N NO.

A E D C - T R - 8 0 - 3 2 I 4 T I T L E ( ~ d Sub(erie)

SUPPLEMENTAL CALIBRATION OF THE AEDC-PWT 16-FT TRANSONIC TUNNEL AERODYNAMIC TEST SECTION

? A U T H O R ( I )

M. L. Mills, ARO, Inc., a Sverdrup Corporation Company

9 P E R F O R M NG O R G A N I Z A T I O N N A M E A N D A D D R E S S

Arnold Engineering Development Center/DOT Air Force Systems Command Arnold Air Force Station, TN 37389

I I C O N ' R O L L I N G O F F I C E N A M E A N D A D D R E S S

Arnold Engineering Development Center/DOS Air Force Systems Command Arnold Air Force Station, TN 37389

14 M O N I T O R I N G A G E N C Y N A M E m. A D D R E S S ( I / dll ferenl Irom ConlroJIIna Ot.hce)

16 D I S T R I B U T I O N S T A T E M E N T (e l this Repot( )

READ INSTRUCTIONS BEFORE COMPLETING FORM

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10 PROGRAM ELEMENT, P R O J E C T . TASK A R E A & WORK U N I T NUMBERS

P r o g r a m E l e m e n t 6 5 8 0 7 F

12. R E P O R T D A T E

July 1981 IS NUMBER O F P A G E S

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I8 S U P P L E M E N T A R Y N O T E S

Available in Defense Technical Information Center (DTIC).

19 K EY WORDS (ConHnue on reverse mlde J! n e c e s s e ~ end |denfHy ~ bJock n ~ b e r )

wind tunnels power consumption wind tunnel nozzles humidity supersonic ~]ow plenum chamber calibration Math number

20 A B S T R A C T (Cont inue on reverse side I f necessary end Jdenlafy by brock number)

A test was conducted in the Propulsion Wind Tunnel (16T) to: (i) define the effect of plenum suction utilization on the tunnel calibration and power consumption at free-stream Mach numbers less than 0.75, (2) improve the centerline Math n~mber calibration at supersonic Mach numbers, (3) correlate the test section centerline Mach number with the tunnel nozzle Mach number, and (4) investigate the effect of tunnel humidity on the calibration. Data were

F O R M 1473 E D , T , O N O F ! N O V S r' IS O B S O L E T E DD i jAN ?,

UNCLASSIFIED

UNCLASSIFIED

20 . ABSTRACT ( C o n t i n u e d )

a c q u i r e d f o r Mach n u m b e r s f r o m 0 . 6 t o 1 . 6 a t t o t a l p r e s s u r e s f r o m 400 t o 3 , 2 0 0 p s f a . T h e c a l i b r a t i o n was c o n d u c t e d i n t h e a e r o d y n a m i c t e s t s e c t i o n u s i n g a c e n t e r l i n e p i p e and w a l l p r e s s u r e o r i f i c e s t o d e f i n e t h e Mach n u m b e r d i s t r i b u t i o n s . The r e s u l t s o f an e v a l u a t i o n o f a l t e r n a t e m e t h o d s o f c a l i b r a t i o n i n d i c a t e d t h a t t h e c u r r e n t m e t h o d i s t h e m o s t a c c e p t a b l e . S l i g h t l y c h a n g i n g t h e t u n n e l n o z z l e t o e l i m i n a t e t h e d i s t u r b a n c e s i n t h e f l o w a t s u p e r s o n i c Mach n u m b e r s i n d i c a t e d t h e n e e d t o i n v e s t i g a t e t h e e n t i r e n o z z l e s y s t e m . C o m p a r i s o n o f t h i s c a l i - b r a t i o n w i t h p r e v i o u s c a l i b r a t i o n r e s u l t s i n d i c a t e s t h a t a r e v i s i o n o f t h e c u r r e n t t u n n e l c a l i b r a t i o n i s n o t n e c e s s a r y .

A F S C A r ~ l d AFS "Jre~

UNCLASSIFIED

A E D C-T R -80-32

PREFACE

The work reported herein was conducted by the Arnold Engineering Development Center (AEDC), Air Force Systems Command (AFSC), at the request of the AEDC Directorate of Test (DOOP) and the AEDC Directorate of Technology (DOT). The Air Force project managers were Capt. Greg Cowley (AEDC/DOOP) and Mr. E. R. Thompson (AEDC/DOT). The results were obtained by ARO, Inc., AEDC Group (a Sverdrup Corporation Company), operating contractor for the AEDC, AFSC, Arnold Air Force Station, Tennessee, under ARO Project Numbers P41T-D4G and P32D-85C. The manuscript was submitted for publication on July 21, 1980.

AEDC-TR-80-32

C O N T E N T S

Page

1.0 I N T R O D U C T I O N ........................................................ 7

2.0 A P P A R A T U S

2.1 Tes t Facil i ty .......................................................... 8

2.2 Ca l ib ra t ion E q u i p m e n t ................................................. 9

2.3 In s t rumen ta t i on ....................................................... 9

3.0 P R O C E D U R E

3.1 Tes t Cond i t i ons ....................................................... l 0 3.2 Da t a Reduc t ion ....................................................... l l

3.3 Unce r t a in ty o f Measuremen t s ........................................... 12

3.4 F low Qual i ty ......................................................... 12

4.0 R E S U L T S A N D D I S C U S S I O N

4.1 Mach N u m b e r Dis t r ibut ions ..................................... ' . . . . . . . 13

4.2 Tunne l Cal ibra t ion .................................................... 17

5.0 C O N C L U S I O N S ......................................................... 20

R E F E R E N C E S ........................................................... 20

I L L U S T R A T I O N S

Figure

1. T u n n e l 16T Test Sect ion and Center l ine P ipe Insta l la t ion . . . . . . . . . . . . . . . . . . . . . . . . 23

2. Tunne l 16T Cal ib ra t ion Insta l la t ion .......................................... 24

3. Nozzle Stat ic Pressure Ori f ice Loca t ions ...................................... 27

4. Tes t Sect ion Wall Angle Schedules . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

5. Var ia t ion o f Tunne l Pressure Rat io with 0 = 0 ................................. 30

6. T u n n e l ' 1 6 T Mach N u m b e r Dis t r ibut ions at M = = 0.6 to 1.0

with X = X*, 0 = 0, and Pt = 1,600 psfa ...................................... 3 !

7. Tunne l 16T Mach N u m b e r Dis t r ibut ions at M = = 1.1 to 1.6

with ~, = X*, 0 = 0, and Pt = 1 ,600ps fa ...................................... 36

8. Ef fec t o f Orif ice Select ion on the Mach N u m b e r Devia t ions

with X = X*, 0 = 0, and Pt = 1,600 psfa ...................................... 41

9. Ef fec t o f Tes t Region Loca t i on on the Mach N u m b e r Devia t ions

with X = X*, 0 = 0, and Pt = 1,600 psfa ...................................... 42

10. Ef fec t o f Center l ine Pipe Length on the Mach N u m b e r Dis t r ibut ions

f r om M® = I. 1 to 1.6 with k = )~*, 0 = 0, and Pt = 1,600 psfa . . . . . . . . . . . . . . . . . . 43

A EDC-TR-80-32

Figure Page

1 I. Effect of Centerline Pipe Length on the Mach Number Deviations

with ) ̀ = )`*, 0 = 0, and Pt = 1,600 psfa ...................................... 44

12. Effect of Mach Number on the Centerline Mach Number Deviations

with )` = )`*, 0 = 0, and Pt = 1,600 psfa ...................................... 45

13. Effect o f Plenum Chamber Suction on the Centerline Mach Number

Distributions at Pt = 1 , 0 0 0 psfa with 0 = 0 ................................... 46

14. Effect of Plenum Chamber Suction on the Centerline Mach Number

Distributions at Pt = 1,600 psfa with 0 = 0 ................................... 49

15. Effect o f Plenum Chamber Suction on the Centerline Mach Number

Distributions at Pt = 2,200 psfa with 0 = 0 ................................... 52

16. Effect of Tunnel Pressure Ratio on the Total Power Factor

at Moo _< 0.75 with 0 = 0 ................................................... 55

17. Effect o f Test Section Humidi ty on the Mach Number Distributions

with )` = )`* and 0 = 0 ..................................................... 56

18. Effect o f Test Section Humidity on the Average Mach Number

with )` = k * a n d 0 = 0 ..................................................... 61

19. Effect o f Test Section Humidi ty on the 2a Mach Number Deviations

with ) ̀ = )`* and 0 = 0 ..................................................... 63

20. Nozzle Wall Mach Number Distributions at Ma = 0.6008 and

Mc = 0.5912 with )` = k*, 0 = 0, and Pt = 1,600psfa . . . . . . . . . . . . . . . . . . . . . . . . . . 65


Mc = 0.7989 with k = ) ,* , 0 = 0, and Pt = 1,600 psfa . . . . . . . . . . . . . . . . . . . . . . . . . . 66


Mc = 0.9859with)` = )~*, 0 = 0, and Pt = 1,600 psfa . . . . . . . . . . . . . . . . . . . . . . . . . . 67~


Mc = 1 . 1 8 6 8 with )` = ) `* , 0 = 0, and Pt = 1 , 6 0 0 psfa . . . . . . . . . . . . . . . . . . . . . . . . . . 69


Mc = 1.3853 with )` = )`*, 0 = 0, and Pt = 1,600 psfa . . . . . . . . . . . . . . . . . . . . . . . . . . 71


Mc = 1.5847 with), = ),*, 0 = 0, and Pt = 1,600 psfa . . . . . . . . . . . . . . . . . . . . . . . . . . 73

26. Tunnel 16T Mach Number Calibration with ), = )`*, 0 = 0,

and Pt = 1,600 psfa ....................................................... 75

27. Tunnel 16T Pressure Calibrations from M® = 0.6 to 1.6

with )` = )`*, 0 = 0, and Pt = 1,600 psfa ...................................... 76

28. Effect o f Nozzle Jack Perturbations on the Nozzle-Test Section

Calibration with ), = )`*, 0 = 0, and Pt = 1,600 psfa . . . . . . . . . . . . . . . . . . . . . . . . . . . 79

A E D C-T R -80-32

Figure Page

29. Effect of the Calibration Method on the Uncertainty of the

Calibrated Free-Stream Static Pressure with 0 = 0 . . . . . . . . . . . . . . . . . . . . . . . . . . . 80

30. Effect of the Calibration Method on the Uncertainty of the

Calibrated Free-Stream Mach Number with 0 = 0 . . . . . . . . . . . . . . . . . . . . . . . . . . . . 83

31. Effect o f Mach Number on the Calibration with X = X*, 0 = 0,

and Pt = 1,600 psfa ..................................................... 86

32. Effect of the Centerline Pipe Length on the Calibration with

X = ~,*, 0 = 0, and Pt = 1,600 psfa ........................................ 87

33. Effect o f Plenum Chamber Suction on the Calibration at M= _< 0.75

with X = )~*, 0 = 0, and Pt = 1,600 psfa .................................... 88

34. Effect o f Test Section Humidity on the Mach Number Calibration

with k = X * , 0 = 0 ...................................................... 89

A P P E N D I X

A. NOZZLE JACK PERTURBATIONS ..................................... 93

N O M E N C L A T U R E .................................................... 108

A E DC-TR -80-32

1.0 INTRODUCTION

The AEDC Propulsion Wind Tunnel (16T) was put into operation in July 1956. Initially,

tunnel calibrations were conducted for the two test sections (aerodynamic and propulsion)

available for tests, but later tunnel or equipment modification, the resolution of the effect of

some tunnel parameter, or the need for improved data quality precipitated several additional

tunnel calibrations. Collectively, this early calibration work revealed that, within the existing

data accuracy, only test section wall angle variation had a significant effect upon the tunnel calibration.

After the installation of fiberglass compressor blades in Tunnel 16T in 1965, a

calibration was conducted with the aerodynamic test section. This calibration (Ref. 1) was

based on pressure orifices located in a 2-ft-wide solid plate in the test section floor. The Ref. l calibration remained in use in Tunnel 16T until May 1977.

To support a program for improving nozzle/afterbody (NAB) test techniques, tests were

conducted in the propulsion test section of Tunnel 16T to determine the tunnel calibration

and centerline Mach number distributions at various test section wall porosities and

Reynolds numbers. During the porosity calibration (Ref. 2), limited data obtained at M,~ =

0.6 and 0.8 indicated that the calibrated Mach number increased slightly (less than 0.001 per

million) with increasing Reynolds number. Following the calibration reported in Ref. 2, an

analysis of the effects of variation of the tunnel calibration with Reynolds number on NAB

test data was conducted. This analysis revealed that a 0.2-percent error in static pressure

attributed to use of the Ref. l calibration, which neglects the effects of Reynolds number,

could cause a 70-drag-count (based on maximum model cross-sectional area) error in nozzle

afterbody drag at M~ = 0.6 and Re = 5.0 x 106/ft. Consequently, a test was conducted to

define completely the effects of Reynolds number variation on the Tunnel 16T calibration.

The results of this calibration, which was conducted with the propulsion test section, are presented in Ref. 3.

Since nozzle afterbody data are sensitive to small changes in the tunnel calibration, the

adequacy of using the same tunnel calibration for both the aerodynamic and propulsion test

sections came into question. Data obtained parasitically during an NAB test in the

aerodynamic test section showed that the effects of Reynolds number on the tunnel

calibration were more pronounced in the aerodynamic test section than in the propulsion

test section. These results precipitated two calibration entries in the aerodynamic test

section. Calibration results, which are reported in Ref. 4, confirmed that the aerodynamic

and propulsion test sections had different Reynolds number effects. Both the Refs. 3 and 4 calibration results are currently utilized for Tunnel 16T operation.

A E DC-T R -80-32

The data in Ref. 4 indicated anomalies in the centerline distributions at supersonic Mach numbers. These anomalies were assumed to be partially attributable to disturbances

originating on the ogive nose of the calibration pipe. The Ref. 4 calibration also indicated that power savings were available by increasing plenum chamber suction at Mach numbers

less than 0.75. However, the Ref. 4 data were insufficient for a complete definition of this

effect. Because of the increasing costs of energy and the need to continually improve the

calibration accuracy, the need for another calibration evolved. This calibration was conducted in the aerodynamic test section using the Ref. 4 calibration pipe and a longer version. In addition to the supersonic disturbances and the plenum suction study, several

other effects in the aerodynamic test section were investigated. These included evaluating the effect of test section humidity on the calibration and defining the correlation between nozzle wall and centerline static pressures.

During the calibration, data were obtained at free-stream Mach numbers from 0.6 to 1.6 at free-stream stagnation pressures from 400 to 3,200 psfa. The effect of plenum chamber suction on power was determined at free-stream Mach numbers of 0.6, 0.7, and 0.75 for

stagnation pressures of 1,000, 1,600, and 2,200 psfa. Test section humidity was varied from

a maximum of 0.009 to a minimum of 0.0005 lb H20/lb dry air, depending upon the test condition. Results from this calibration are presented in this report.

2.0 APPARATUS

2.1 TEST FACILITY

The AEDC Propulsion Wind Tunnel (16T) is a variable density, continuous-flow tunnel capable of being operated at Mach numbers from 0.2 to 1.6 and stagnation pressures from 120 to 4,000 psfa. The maximum attainable Mach number can vary slightly depending upon

the tunnel pressure ratio requirements with a particular test installation. The maximum

stagnation pressure attainable is .a function of Mach number and available electrical power.

The tunnel stagnation temperature can be varied from about 80 to 160°F depending upon the cooling water temperature. The tunnel is equipped with a scavenging system which

removes combustion products when rocket motors or turbo-engines are tested. The test section is 16 ft square by 40 ft long; it is enclosed by 60-deg inclined-hole perforated walls of six-percent porosity. The test section sidewalls can be either converged 2 deg or diverged 1 deg. The general arrangement of the test section and perforated wall geometry is shown in Fig. 1.

To prevent tunnel choking in the transonic Mach number range, test section flow removal is accomplished with a plenum evacuation system (PES), which is also utilized to

control tunnel pressure level. The PES compressors are driven by motors with a total power

rating of 179,000 hp, and the tunnel main compressor drive system is rated at 226,000 hp.

A E DC -TR -80-32

Various Mach numbers in Tunnel 16T are established by regulation of tunnel pressure

ratio, plenum pressure, and the contour of a flexible, two-dimensional Laval nozzle. Mach

numbers below 0.55 are obtained by operating the compressor drive motors subsynchronously. Test section flow removal is normally required at M® > 0.75 and

supersonic nozzle contours are used at Moo _> 1.05. Additional details concerning Tunnel 16T and its capabilities are presented in Ref. 5.

2.2 CALIBRATION EQUIPMENT

A 6.5-in.-diam static pressure pipe was used to obtain the centerline static pressure distribution from tunnel station -5.9 to 24.1. The aft end of the calibration pipe was

attached to the tunnel sting support system, and a mechanism was provided to counteract

pipe sway and sag. Four cables, swept rearward at 30 deg to the tunnel centerline and spaced to produce a moment that would aid in removing pipe sag, provided pipe support. The pipe,

which had an ogive tip, was subject to a tensile load by a cable which extended upstream into the tunnel nozzle and connected to a streamlined forebody and cable support system. The

pipe installation is shown in Fig. 2. To improve the supersonic Mach number distributions,

the nose of the existing static pressure pipe was extended from station -22 to -30. After the

effect of pipe length on the test section Mach number distribution was determined, the 8-ft

extension was removed so the final pipe configuration was the same as that used on previous calibration tests.

2.3 INSTRUMENTATION

The centerline pipe contained 75 static pressure orifices (0.127-in.-diam), fifty-four of

which were located approximately 30 deg in a clockwise direction (facing upstream) from the

vertical plane and referred to as the centerline pipe upper orifices. These orifices were spaced

in 1-ft intervals from tunnel stations -5.9 to 0. I and 0.5-ft intervals from tunnel stations 0. I

to 24.1. The remaining 21 orifices were located approximately 210 deg in a clockwise

direction (facing upstream) from the vertical plane.and referred to as the centerline pipe

lower orifices. These orifices were spaced in l-ft intervals from tunnel stations 0. ! to 20. I.

Test section wall static pressure distributions were obtained from three rows of orifices

(Fig. 1). A row of 20 orifices (0.065-in.-diam) was located 1 ft west of the tunnel centerline in

the porous floor plates and spaced in 1-ft intervals from tunnel stations 1 to 20. A row of 24

orifices (0.065-in.-diam) was located 1 ft east of the tunnel centerline in 2-ft-wide solid floor

plates. The solid floor was extended upstream to tunnel station -9 by filling all holes in the single transition section taper strip as shown in Fig. 2. These orifices were spaced in l-ft

intervals from tunnel stations 0 to 20 and 2-ft intervals from stations 20 to 26. Another row

9

A E DC-TR-80-32

of 20 orifices (0.65-in.-diam) was located 1 ft west of the tunnel centerline in porous ceiling

plates. These orifices were spaced in l-ft intervals from tunnel stations l to 20.

Nozzle wall static pressures were measured with 12 orifices (0.125-in.-diam) at tunnel

station -4, 5 orifices (0.125-in.-diam) at tunnel station -8, and 8 orifices (0.125-in.-diam) at tunnel station -12 as shown in Fig. 3.

The pipe, wall, and nozzle orifices were connected to differential pressure transducers

referenced to the tunnel plenum chamber pressure. The tunnel stagnation pressure was

determined by averaging measurements from two independent systems of total pressure

probes installed in the tunnel stilling chamber. The plenum chamber and stagnation

pressures were determined by measurements from Datametrics ® pressure transducers.

3.0 PROCEDURE

3.1 TEST CONDITIONS

The calibration was conducted over a Mach number range from 0.6 to 1.6, although

special emphasis was placed on the effects of plenum suction at 0.6 _ M= _ 0.75 and on

the quality of the supersonic Mach number distributions at M.. _> 1.2. Data were obtained

at various stagnation pressures from 400 to 3,200 psfa and at a stagnation temperature o f

110°F, which corresponds to a unit Reynolds number variation from 0.6 x 106/ft to 4.9 x

106/ft. The effects of tunnel pressure ratio, test section wall angle variation, and nozzle jack

movements were evaluated at a stagnation pressure of i ,600 psfa. A stagnation pressure of

i ,600 psfa was chosen as a baseline for data acquisition because previous calibrations (Refs.

3 and 4) were conducted primarily at 1,600 psfa. The effects o f tunnel specific humidity variation were evaluated at Mach numbers of 0.6, 0.9, 1.2, and 1.5.

The test section wall angle was varied from 0.50 to -1.00 deg. Positive wall angles

correspond to wall divergence from the tunnel centerline. The Tunnel 16T opt imum wall

angle schedule and the range of wall angles investigated during this calibration are shown in

Fig. 4. The opt imum wall angle schedule generally provides the "bes t " pressure distribution

on long, slender bodies of revolution with a test section blockage of one percent.

On the basis of data presented in Refs. :3 and 4, a nominal pressure ratio schedule was used during variations o f test section wall angle and Reynolds number. The nominal

pressure ratio (X*) schedule is shown in Fig. 5. To determine the effects o f pressure ratio on the Mach number distributions, the pressure ratio was varied above and below the nominal

10

A EDC-TR-80-32

schedule at M** = 0.8, 0.9, and 1.0. To determine the effect of using plenum suction on

tunnel power requirements at M** = 0.6, 0.7, and 0.75, the tunnel pressure ratio was decreased below the nominal schedule.

The effect of specific humidity variation on the calibration was obtained by "wett ing"

the tunnel to the maximum specific humidity obtainable and then taking data while the tunnel was drying. The maximum range of specific humidity was from 9.0 x 10-3 to 0.5 x

10-3 lb H20/lb dry air. For most other test conditions the specific humidity was maintained at less than 1.5 x 10 -3 lb/Ib.

In an attempt to eliminate the data anomalies at supersonic Mach numbers reported in Ref. 4, the centerline pipe was extended to tunnel station -30 by placing an 8-ft extension

immediately aft of the ogive tip. After observing that the "longer" pipe did not improve the

Mach number distributions, the extension was removed for the remainder of the test. To investigate the influence that the Tunnel 16T nozzle has on the supersonic data anomalies, data were obtained with individual nozzle jacks perturbed slightly from the design contour. Nozzle jacks were moved up to 0.35-in. from the nominal contours.

3.2 DATA REDUCTION

The distribution of local Mach number in the test section was obtained from the centerline pipe and wall static pressure data with the assumption of isentropic flow through the nozzle. The average Mach numbers and the 20 Mach number deviations for three test section regions, tunnel stations I to 20, 3 to 19, and 6 to 18 were computed. The Mach number deviation, 20, is the conventional two standard deviation parameter used in

statistical analysis. Nozzle average Mach numbers were computed using rings of nozzle wall

static pressure orifices located at tunnel stations -12, -8, and -4.

The calibration of Tunnel 16T is based on the measured pressure differential between the

test section and the plenum chamber at various operating conditions. An equivalent plenum chamber Mach number is calculated from plenum chamber and tunnel stagnation pressure measurements using the isentropic relationship. A calibration parameter, defined as the difference between the free-stream and plenum chamber Mach numbers (Ma - - Me), is used to express the tunnel calibration for various operating conditions.

To aid in evaluating potential improvements in the accuracy of the calibration, three other calibration parameters were computed. A calibration factor, defined as the difference

between the free-stream static and plenum chamber pressures normalized by free-stream stagnation pressure (Pa - - Pc)/P.t, was used. This calibration factor provides static pressure

II

A EDC-TR-80-32

directly as a function of the plenum chamber pressure. Mach number is determined using

isentropic relationships between p** and Pt. The calibration factor (Pa - - Pnozzle.)/Pt, which would make the tunnel calibration independent of the plenum chamber pressure and the calibration factor (Pa/Pt), was also investigated.

3.3 UNCERTAINTY OF MEASUREMENTS

A Taylor series method of error propagation was used to estimate the uncertainty in the calibration parameters which could be attributed to instrumentation errors and data

acquisition techniques. Uncertainties in the instrumentation systems were estimated from repeat calibration of the systems against secondary standards whose uncertainties are traceable to the National Bureau of Standards calibration equipment. For a confidence level

of 95.4 percent, the estimated uncertainties are:

Parameter Uncertainty

±0.002

0 ±0.04 deg

±0.003 Mlocal

M ±0.0006 a

P ±0.73 psf a

Re ~0.02 x 10-6/ft

(M a - Mc ) ±0.0014

(Pa - Pc)/Pt ±0.0009

Pa/Pt ±0.0008

(Pa - Pnozzle)/Pt ±0.0008

3.4 FLOW QUALITY

One of the primary objectives of a tunnel calibration is to ascertain that adequate flow

quality exists for acquisition of test data for various locations of test models and various

combinations of tunnel conditions. Tunnel flow quality encompasses several parameters,

such as flow angularity and turbulence, which were not investigated during this calibration.

12

A EDC-TR-80-32

Past calibrations have indicated that axial pressure gradients requiring the application of

buoyancy corrections to test data do not exist in Tunnel 16T for normal operating conditions. This report, therefore, is concerned only with the uniformity of the axial Mach number distributions.

A quantitative evaluation of the uniformity of a Mach number distribution, when no pressure gradients exist, can be p, rovided by analysis of the 2a Mach number deviation. This

deviation can also be used to evaluate the effects of various test parameters on the centerline Mach number distributions. The minimum Mach number deviation for a particular test section length and set of tunnel conditions is, of course, indicative of the "best" distribution. For purposes of this report and in conformity with Refs. 3 and 4, 2~ Mach number

deviations of 0.005 Moo and 0.01 Moo for subsonic and supersonic Mach numbers, respectively, will be used as criteria for relative evaluation of the various Mach number distributions. These criteria should not be confused with tunnel data quality goals and requirements, which "are established by individual test objectives.

4.0 RESULTS AND DISCUSSION

4.1 MACH NUMBER DISTRIBUTIONS

4.1.1 General

Typical short pipe centerline and wall Mach number distributions obtained at Mach numbers from 0.6 to 1.6 with )~ = X*, 0 = 0, and Pt = 1,600 psfa are presented in Figs. 6 and 7. The data presented in Fig. 6 indicate that at subsonic Mach numbers, the Mach number distributions on the centerline and tunnel walls differ aft of tunnel station 20. The differences are attributed to different interference and plenum chamber suction effects. The centerline pipe pressures are predominantly affected by boom flare and support strut

interference, which cause a deceleration of the flow. The wall distributions are

predominantly affected by strut interference, wall bulge, and plenum suction. The local

Mach number along the solid plate also increases aft of tunnel station 20 at Moo < 0.8 and

decreases at Moo > 0.8. This is attributed to the use of plenum chamber suction which began at Moo = 0.8.

The data presented in Fig. 7 indicate that at supersonic Mach numbers the forward portions of the centerline and wall distributions differ. According to Refs. 3 and 4, for

which similar Mach number distributions were obtained, the supersonic centerline Mach number distributions were believed to be affected by disturbances which emanated from the forward portion of the calibration pipe and from near tunnel station 0. During this test, an

13

AE DC-TR-80-32

attempt was made to eliminate these anomalies by extending the calibration pipe. These results are discussed in Section 4.1.2 of this report.

The 2a'Mach number deviations for various test regions may be used as an aid in

evaluating the Math number distributions. The effects of pressure orifice selection and test region length are illustrated in Figs. 8 and 9. The comparisons of the deviations for various test region lengths have the same variation, in general, as the Ref. 4 data. The upper

centerline pipe data from tunnel stations 6 to 18 are considered the primary data to be used as the basis for the calibration for the same reasons as reported in Ref. 4.

The effects of varying tunnel pressure ratio and test section wall angle on the Mach number distributions and 2a Mach number deviations were essentially the same as those reported in Ref. 4 and are therefore not presented here.

4.1.2 Effect of Calibration Pipe Length

In an attempt to eliminate the disturbances in supersonic Mach number distributions, the calibration pipe was extended 8 ft. This extension caused the pipe nose shock to impinge on the nozzle walls rather than the test section walls. Similarly, the shock reflection from the nozzle walls impinged on the calibration pipe upstream of station 0.

Comparisons of the Mach number distributions and 2a Mach number deviations for the calibration pipe with and without the pipe extension (hereafter referred to as the long and short pipe) are presented in Figs. 10 and 11. The data in Fig. 10 indicate pipe length has large

effects on the distribution upstream of tunnel station 0 with smaller effects in the primary test region which are not noticeable in Fig. 10 but indicated by the 20 deviations in Fig. 11.

The data in Fig. 11 indicate that there is no difference between the short and long pipe deviations at Mach numbers from 0.8 to !.0. With the exception of M** = !. 1, there are

only small but inconsistent differences between the short and long pipe deviations at supersonic Math numbers. Since the longer pipe did not significantly improve the centerline

distributions, the short pipe configuration was used for most of the calibration test so that a direct comparison could be made with previous data. Data were not taken with the short

calibration pipe configuration at M** = 0.6, 0.7, and 0.75 after observing that no change occurred in the other subsonic Math number distributions when using the long pipe.

14

A EDC-TR-80-32

4.1.3 Effect of Mach Number

The effect of Mach number on the 2a Mach number deviations for the centerline distributions and a comparison with the Ref. 4 calibration are shown in Fig. 12. The data

indicate that, except for M® = ! .2 and 1.6, the deviations are better than the relative criteria

for " g o o d " distributions. The disturbances causing the poor Mach number distributions were previously thought to originate on the calibration pipe, but the Ref. 4 data in Fig. 12

and the current data were obtained with the same centerline pipe installation. The fact that

poorer quality data were obtained at M~ = 1.2 and 1.6 indicates that other disturbances

exist in Tunnel 16T which affect the quality of the Mach number distributions. This

observation led to an attempt to eliminate the disturbances by perturbating individual nozzle jacks. These results are presented in Appendix A.

4.1.4 Effect of Plenum Suction

The effect of using plenum suction on the centerline distributions at Moo _< 0.75 with

Pt = 1,000, 1,600, and 2,200 psfa are shown in Figs. 13, 14, and 15. The flow decelerates aft

of tunnel station 20 when tunnel pressure ratio is decreased to accommodate the increased

plenum suction. The data quality is slightly improved when using plenum suction, except at

M® = 0.6, Pt = 2,200 psfa, as indicated by the 2t~ deviations.

The effect of plenum suction on tunnel power requirements at Moo _< 0.75 is presented in Fig. 16. These data were obtained with the plenum bypass valve (Valve 12) both opened and

closed. For the Valve 12 open cases, the power data were not corrected by subtracting the

power associated with flow recirculated through the PES via Valve 12. The data show a

minimum power requirement when tunnel pressure ratio is reduced by 0.5 percent at M® =

0.6 and 0.7 and by 1.5 percent at Moo = 0.75 for Pt = 1,600 psfa. Further decreases of tunnel pressure ratio, which coincide with increasing plenum suction, cause an increase of

total power. Based on the data at Pt = 1,600 psfa, the data for Pt = 1,000 and 2,200 psfa

were taken at tunnel pressure ratios which were too low to define the minimum total power

requirements. Thus, further data are required for a complete deffnition of the range of tunnel pressure ratios or wall suction which will minimize power.

4.1.5 Effect of Humidity

The effect of test section humidity on the Mach number distributions, the average Mach

number of the primary test region (tunnel stations 6 to 18), and the 2a Mach number

deviations for various tunnel conditions is shown in Figs. 17, 18, and 19. The objectives of

the humidity study were to determine if humidity has an effect on the tunnel calibration and

]5

A EDC-TR-80 -32

if the present dryness criteria for Tunnel 16T are acceptable. The data presented in Figs. 17,

18, and 19 indicate that, for the range of humidities investigated, humidity does not have a significant effect upon the Mach number distributions, except at M= = 1.5.

The current dryness criteria are that the test section static temperature must be greater

than or equal to the test section dew point temperature for subsonic operation, and the

specific humidity must be less than 0.0015 lb H20/ lb dry air for supersonic operation.

The data in Figs. 18a-b and 19a-b show that data were not obtained at humidities which exceed the subsonic dryness criteria at M= = 0.6, Pt = 3,200 psfa, and M® = 0.9, Pt =

1,200 psfa. However, this is not significant because the full range of possible humidities

encountered during tunnel operations was obtained. There is no observable humidity effect

for this range at M® = 0.6, Pt = 3,200 psfa, and M® = 0.9, Pt = 1,200 psfa.

The data in Figs. 18c-d and 19c-d indicate that there is no humidity effect on the average Mach number or the 2o Mach number deviations at M= = 0.9, Pt = 2,400 psfa and M® =

1.2, Pt = 1,600 psfa while the tunnel is operating within or slightly above the dryness criterion limit.

The data presented in Fig. 17e indicate that humidity has an effect on the Mach number

distribution at M= = ! .5. There is a positive Mach number gradient through the test section

with the local Mach number increasing to !.5 in the downstream end of the test section. This

effect is also indicated by decreasing average Mach numbers and increasing 20 deviations

with increasing humidity as shown in Figs. 1Be and 19e. Throughout the humidity run, the

plenum chamber pressure and stagnation pressure were not allowed to vary. The probable

explanation for the effects cited above is that a condensation shock formed in the tunnel

nozzle, causing the flow to decelerate, as indicated by the distribution in Fig. 17e. The

porous test section walls permit the flow to expand to the plenum chamber pressure, which

causes a Mach number gradient through the test section. The Mach numbers calculated when a condensation shock is present are not valid, however, because the stagnation

pressure used to calculate Mach number is measured upstream of the shock. The data in

Figs. 18e and 19e indicate that the Mach number distributions are not affected when the

humidity is less than the dryness criterion limit. Thus, the test section humidity should never be allowed to exceed the dryness criterion during testing at M= = 1.5.

4.1.6 Nozzle Wall Mach Number Distributions

Typical Mach number distributions measured on the tunnel nozzle walls at tunnel stations -4 and -12 are presented in Figs. 20 through 25. The data indicate that the local

16

A EDC-TR-80-32

Mach number varies less at tunnel station -12 than at -4 for subsonic Mach numbers as

indicated by the 2a deviations. These variations may be due to orifice or local surface

irregularities such as the porous hole patterns at tunnel station -4, paint roughness, and

mounting bolts countersunk in wall plates upstream of tunnel station -4. At supersonic

Mach numbers the 2a deviations are smaller at tunnel station -4 than at -12. The variations in

wall Mach number at supersonic Mach numbers are caused by the same disturbances as for

subsonic Mach numbers plus spurious wave patterns emanating from the centerline pipe or

nozzle walls.

The 2a deviations indicated in Figs. 20 through 25 are larger in general than those of the

calibration pipe data presented in Fig. 12. This makes a correlation between the nozzle and

test section Mach numbers undesirable for use as a calibration of Tunnel 16T.

4.2 TUNNEL CALIBRATION

4.2.1 General

Analytic expressions of the Mach number calibration parameter ( M a m Me) as a function

of equivalent plenum chamber Mach number, test section wall angle, and Reynolds number

are currently used to express the Tunnel 16T calibration. These expressions were obtained by

using a least-squares, multiple regression data fitting program and are incorporated into the

facility computer.

The use of tunnel calibration factors (Pa - - Pe)/PI, P,t/Pt, and (Pa - - Pnozzle)/Pt, to express the calibration was investigated in an attempt to improve the accuracy of the tunnel

calibration and possibly remove the effects of test section wall angle and Reynolds number

from the calibration. Pressure calibrations were used rather than Mach number calibrations

to determine if the estimated uncertainty of the test section calibrated static pressure can be

improved by calculating the static pressure directly.

The tunnel Mach number calibration parameter and the three tunnel pressure calibration factors are determined from measurements of the tunnel test section static, stagnation, and

either plenum chamber or nozzle static pressures. These pressures have different control and

measurement response characteristics. The plenum chamber and stagnation pressures are

independently and manually controlled, but the control of all four pressures are interrelated

because the test section and plenum chamber communicate through the ventilated walls.

Thus, the calibration parameter and factors are very sensitive to transients in various tunnel

parameters. Most of the data scatter exhibited in the calibration data presented herein is

attributed to such control transients. During acquisition of data at each test condition, data

17

A E D C -T R -8 0 -3 2

points were obtained until the tunnel calibration parameter had been repeated or the data

scatter had been bracketed. Three data points were required for most test conditions. As

indicated in Section 4.1. l, the calibration data presented herein are based on centerline pipe data obtained for the primary test region, tunnel stations 6 to 18.

4.2.2 Alternate Calibration Factors

The current tunnel Mach number calibration parameter is presented in Fig. 26 and three alternate tunnel pressure calibration factors with X = X*, 0 = 0, and Pt .-- 1,600 psfa are

presented in Fig. 27. "i'he factor (Pa - - Pc)/P,, (Fig. 27a) is the pressure equivalent o f the

Mach number calibration parameter (Ma - - Me). The factor (Pa/Pt) (Fig. 27b) is monotonic,

increasing as the ratio of Pc/Pt increases. The factors, (Pa - - Pnozzle)/Pt, relating the test section static to nozzle static pressure at tunnel stations -4 and -12 are presented in Figs. 27c

and d, respectively. The points in Fig. 27c which correspond to Mach numbers of 1.2 and 1.5

and in Fig. 27d which correspond to Mach numbers !.2, 1.4, and 1.5, deviate significantly from what would be expected. Some improvement was gained by perturbing nozzle jack 1

and by perturbing nozzle jacks 2 and 4 at M® = 1.2 as shown in Fig. 28. The data show

more variation in the calibration factor at tunnel station -12 than at tunnel station -4. The

cause o f the data anomalies at the supersonic speeds needs to be found before a decision

with regard to the utilization of tunnel stations -4 and -12 static pressures for the tunnel calibration can be made.

4.2.3 Pressure and Mach Number Uncertainty

Pressure and Mach number uncertainties were estimated for the calibration parameters

(Ma - - Mc), (Pa - - Pc)/P,, and Pa/Pt. The estimated uncertainty of the calibrated free- stream static pressure and Mach number for stagnation pressures of 1,000, 1,600, and 2,500

psfa and Mach numbers from 0.7 to 1.6 are presented in Figs. 29 and 30, respectively. The estimated uncertainty of the calibrated static pressure increases with increasing stagnation

pressure, whereas the estimated uncertainty of the calibrated Mach number decreases. The

estimated uncertainty of the calibrated static pressure can be decreased from M® = 0.8 to

1.2 by using a pressure calibration rather than a Mach number calibration. However, the estimated uncertainty would increase at M® _< 0.8 and M® _> i.2.

For example, the estimated uncertainty o f the calibrated static pressure is 0.05 psf less at

Moo = 0.9, Pt = 1,600 psfa using the calibration factor (Pa - - Pc)/PI to express the calibration, but 0.04 psf greater at M= = 1.4. There is not a significant effect o f changing

the method of calibration on the calibrated free-stream Mach number uncertainty. The

18

A E D C-T R -8 0-3 2

estimated uncertainty of the calibrated Mach number varies less than 0.0003 with the various

methods of calibration, except at M~, = 0.6 where the estimated uncertainty of the

calibrated Ma~:h number increases by 0.001 when using the pressure calibration methods.

Expressing the calibration of Tunnel 16T as a function of pressure instead of Mach

number does not decrease the estimated uncertainty of free-stream static pressure or Mach number significantly or over a large enough Mach number range. Thus, the calibration of

Tunnel 16T should continue based on the calibration parameter (Ma - - Me).

4.2.4 Effect of Mach Number on the Calibration

Parameter (Ma - - Mc)

The calibration parameter as a function of equivalent plenum chamber Mach number

from M . = 0.6 to 1.6 and the Ref. 4 data are presented in Fig. 31. Although the calibration

has slightly changed, the difference between the current data and the Ref. 4 data is less than

the uncertainty in either data set. The largest difference in Mach number, which is 0.003,

occurs at M,~ = 1.3. This difference in the calibrations at Mach number is not considered large enough to require a change in the tunnel calibration from that reported in Ref. 4.

4.2.5 Effect of Calibration Pipe Length

The effect of the calibration pipe length on the calibration is presented in Fig. 32. Pipe

length has no effect on the calibration at M® = 0.8 to 1.0; thus, it is assumed that there is no

effect at Moo = 0.6 to 0.75. Small effects on the calibration parameter are attributable to pipe length at supersonic Mach numbers, with the largest causing a difference of 0,002 in

Mach number at M~ = 1.6.

4.2.6 Effect of Plenum Chamber Suction at M,,, _ 0.75

The effect of using plenum chamber suction at M~ _< 0.75 on the calibration is shown in

Fig'. 33. The calibration parameter decreases by 0.001 and 0.0007 at Moo = 0.6 and 0.7,

respectively. There is no change in the calibration at Moo = 0.75. The changes cited at M®

= 0.6 and 0.7 are considered insignificant since they are less than the measurement uncertainty in the calibration parameter.

4.2.7 Effect of Humidity on the Calibration

The effect of tunnel humidity on the Mach number calibration parameter is presented in

Fig. 34. During drying of Tunnel 16T at Moo = 0.9 with P~ = 1,200 psfa (Fig. 34b),

difficulty was encountered in stabilizing the control parameters. Consequently, the data

19

AE DC-TR-80-32

obtained at SH x 10+ 3 from 3.5 to 9.1 Ib/lb are omitted because tunnel conditions were

unsatisfactory. The data in Fig. 34 indicate that humidity does not have a significant effect

on the tunnel calibration except at M** = 1.5. However, there is no effect if the humidity is

within the dryness criteria at M= = !.5. Thus, the available data indicate that the tunnel

operation dryness criteria of Tunnel 16T are acceptable with respect to the tunnel

calibration.

5.0 CONCLUSIONS

Based on the results of this Tunnel 16T centerline calibration, the following conclusions have been reached:

I.

.

.

.

.

Extending the centerline calibration pipe by 8 ft did not eliminate the centerline

data anomalies at supersonic Mach numbers (i.e., M= = 1.2).

Tunnel humidity does not affect the tunnel calibration when operating within

the tunnel humidity operating criteria.

A correlation between the test section static pressure and the nozzle static

pressure does not appear feasible for expressing the calibration of Tunnel 16T

until the data anomalies in the nozzle static pressures at supersonic. Mach numbers are eliminated.

The calibration factors Pa/P t and (Pa - Pc)/Pt do not improve the estimated

uncertainty of the calibrated test section static pressure or Mach number. Thus,

there is no clear advantage in using these to express the calibration.

Utilization of plenum suction at M** ~ 0.75 and Pt = 1,600 psfa permitted a

reduction of total power. Data at Pt = 1,000 and 2,200 psfa were

inconclusive. There is no reason to believe that a reduction in total power can be

achieved at Pt = 1,000 and 2,000 psfa and other pressure levels. Thus, further study is recommended.

REFERENCES

I. Gunn, J. A. "Check Calibration of the AEDC 16-Ft Transonic Tunnel." AEDC-

TR-66-80 (AD633277), May 1966.

20

A E D C -T R -8 0-3 2

2. Jackson, F. M. "Calibration of the AEDC-PWT 16-Ft Transonic Tunnel at Test Section Wall Porosities of Two, Four, and Six Percent." AEDC-TR-76-13 (AD-B008985L), January 1976.

3. Jackson, F. M. "Calibration of the AEDC-PWT 16-Ft Transonic Tunnel with the Propulsion Test Section at Various Reynolds Numbers." AEDC-TR-77-121 (AD- A057877), August 1978.

f

4. Jackson, F. M. "Calibration of the AEDC-PWT 16-Ft Transonic Tunnel Aerodynamic Test Section at Various Reynolds Numbers." AEDC-TR-78-60 (AD-A065112), February 1979.

5. Test Facilities Handbook (Eleventh Edition). "Propulsion Wind Tunnel Facility, Vol. 4." Arnold Engineering Development Center, June 1979.

21

bJ "t~J

~ - T y p J c a l P o r o u s P l a t e Pressure Orifice l,ocat~on

l o-I? ~_. ~ l / ~c~" I17 dog

T y p i c a l P e r f o r a t e d W a l l P a t t e r n

Notes:

~ S o l i d F P e r f o r a t e d

~_ ~Cablo [/~j,/~f-6 Orifices, l-ft Sp.~ing

= - - ~ C a b ~ r / / z . i ~ / 48 O r i f i c e s , 0 . 5 - f t S p a c i n g

e I ~ Y ~ ~ 21 Orifices, 1-ft Spacing

U-Extension

I S t a -30

S t a S t a S t a - 2 2 - 1 2 . 3 - 1 0

( 1 ) 20 O r i f i c e s ( S t a 1 t o 2 0 ) I f t Wes t o f F l o o r C e n t e r l i n e i n P o r o u s P l a t e

( 2 ) 24 O r i f i c e s ( S t a 0 t o 26 ) 1 f t E a s t o f F l o o r C e n t e r l i n e i n S o l i d P l a t e

( 3 ) 20 O r i f i c e s ( S t a 1 t o 20 ) 1 f t West o f C e i l i n g C e n t e r l i n e i n P o r o u s P l a t e

~nl { H ~ 17~)cr~H Wn 1 I ~ction c k a g e

r t

I I I I I S t a S t a S t a S t a S t a

0 5 24 28 40

S t a t i o n s i n F e e t

Figure 1. Tunnel 16T test section and centerline pipe installation. m O

=n & o

~J

t ~ J~

~> m

~0 do o

a. Pipe and main supporting cables Figure 2. Tunnel 16T calibration installation.

t~

51

A E D C 12052-79

b. Pipe and forward cable system Figure 2. Continued.

m

Q

. e , , , - . , , .

l

m

1 1 1

o

D

West Wall

f

m ~

"ql

0

8

~ ~ i ~ ~

c. Pipe and aft mount system Figure 2. Concluded.

~i~i~i ~ ~'~ z ~ !z~ ~

A EDC-TR-80-32

t ( 50

46

/_ East Wall

Note:

~ 70

- - - - 0 0

- - ~o~

+

T u n n e l S t a t i o n - 4

-------0 0========0 ---

All Dimensions in Inches

Sketch Not to Scale

-V 46

2 5O

West Wail

E a s t Wall

45

45

+

I Tunnel Station -8

0

45

)

45

West W a l l

a. Tunnel stations -4 and -8 Figure 3. Nozzle static pressure orifice locations.

27

AE DC-TR-80-32

24

t_

E a s t W a l l

~_00 _ ~ ~ 0 _~ - - - - - - O O O - - - - - -

÷

- - - - - O O O - - - - -

24

West W a l l

N o t e ' A l l D i m e n s i o n s i n I n c h e s

S k e t c h No t t o S c a l e

b. Tunnel station -12 Figure 3. Concluded.

28 i

r~ xO

t~0

"0

(Z)

v

o P-4

(¢

P-4

r~

o .rl +~

o

+~ u}

0.8

0.4

-0.4 -

-0.8 -

-1.2 0 .1

L

T e s t E n v e l o p e ~ _ _

1 I I i I ~ i !

I I I ~ I I I , i I . i , " I I i . . i i i I u IJ , j f ! l I I

Optimum Wall Angle ! S c h e d u l e (8*)

I

0 . 3 I I I , , . I I I

0.5 0.7 0 . 9 1.1 1.3 1.5

Mach Number (M~)

Figure 4. Test section wall angle schedules.

I 1 . 7

~> m o o

& C)

~J C~

o

0~

~0

e-

1.5

1.4

1.3

1.2 m

1.1 --

1.0

0.1

- I

O. B

Compressor Stall Limit

v

S~ |

I I

s~_~ x------Test Envelope

With Plenum Suction

"---'--No Plenum Suction

I I I I I

0.5 0.7 0.9 i.I 1.3

Mach Number (Mw)

.Nominal X

I . I

1.5 1.7

~>

m

o

-n

d0 0

Figure 5. Variation of tunnel pressure ratio with 0 = O.

I.i0

S y m b o l M

[ ] 0 . 6 0 1

O 0 . 6 9 8

A 0 . 8 0 0

0 . 9 0 0 V 0 . 9 9 9

,1o e o

J~ o

r , l

o

O0 ~-V--S ,-~-v-.

9 0 - - ~ < I ~ - ' ~ ,~:::'--~

80 --------~ ~ ~

6 0 r.~.

50 - -

II I ~,p,,~ ^^,~,.^^~.~_~^-'._^_^^.~ ̂ _^_,_^_^_~:[-^-_~ ^ ^~_ ,

[ ] ~ :LT ; ; : : : : : : ~ : : - " " ~ i l : ; ~ " P : : " I.." : -'_-" -" : -' -'--'-" . . . . ~ - ' ' -~ -

0 40

3 0 - 8 -4 0 4 8 12 16 20

Tunnel Station, ft

a. Upper centerline pipe Figure 6. Tunnel 16T Mach number distributions at M.. = 0.6 to 1.0

with ~ = ) ,* , 8 = 0, and Pt = 1 ,600 psfa.

24 28 )> m t~ o

do O

i.i0

1.00

O. 90

a)

"~ O. 80

o O . 7 0

i=d

O. 60 o o

O. 50

S_~mbol M

O 0.601

0 0.698

O. 800

<~ O. 900

I

J> m 1:3 0

do 0

O. 40

O. 30 -8 -4 0 4 8 12 16

Tunnel Station, ft

20 24 28

b. Lower centerline pipe Figure 6. Continued.

~ J t~J

1 . 1 0

1.00

O. 90

0 . 8 0

O. 70

0 . 6 0 o o ,-.1

O. 50

0 . 4 0

O. 30

- 8 - 4

Symbol M=

0 0.601

0 0.698

0.800

O. 9 0 0

V 0 . 9 9 9

J ~

. . . . r . . . . . . . .

0 4 8 12

T u n n e l S t a t i o n , f t

c. Bottom wall, solid plate Figure 6. Continued.

]

16 20 24 28

m o f~

& 0

~ J

1.10

Symbol M

[] 0 .601

0 0.698

O.800

0.900

V 0 . 9 9 9

m

o

& 0

1.00

t ~

0;

E

0 . 9 0

O. 80

U O. 70

0 . 6 0 0 o

O. 50

0.40

O- ~ ~- ~-C~<Y-O=<Y-fY~-O -()-0-()-~)-~)-()

O. 30

-8 -4 0

d.

4 8 12


Bottom wall, porous plate Figure 6, Continued.

16 20 24 28

1 . 1 0

Symbol M

[] 0 . 6 0 1

0 0 . 6 9 8

0 . 8 0 0

0 . 9 0 0

V 0 . 9 9 9

1.00 -~" v ~"~ v "~- v ~ v ~ " ~ " ~ V " ~ v ~

t ~

0 . 9 0

O. 80

o O. 70 e~

0 . 6 0 ¢3 o

O. 50

w

0.40

0 . 3 0

- 8 -4 0

e.

4 8 12 16


Top wall, porous plate Figure 6. Concluded.

20 24 28

rn

t~

-n

& 0

~0

CP~ ,.¢:: 0 d

d ¢J 0

,--1

1.70

1.60 --

1.50

1.40

1.30

1.20

1.10

Symbol M°°

0 1.101

0 1. 200

A 1. 300

<~ 1. 400

V 1 .499

I> 1 .600

v -

~ " " ' ' t o O 0 ( } " L ~ : ~ r ~ ' 4

1. O0

~> m 0

k

0

O. 90 - 8 -4

Figure 7.

0 4 8 12 16 20

Tunnel Station, ft

a. Upper center l ine pipe Tunnel 16T Mach number d is t r ibut ions at M = 1.1 to 1.6 wi th ;~ = ~*, 0 = O, and Pt = 1,600 psfa.

24 28

1.70

1 . 6 0

I. 50

~ 1 . 4 0

o 1 . 3 0

1.20 o o

1.10

Symbol M

[] 1. 101

O 1. 200

1. 300

<~ 1 . 4 0 0

V 1 . 4 9 9

1. 600

w - -

\

~ A

i . O0

O. 90

-8 - 4 4 8 12


b. Lower centerline pipe Figure 7. Continued.

16 20 24 28 3> m o ¢1

:0 & O

~J

L~

O0

i. 70

1.60

k O~

E

J~ o

p~

0

1.50

1 . 4 0

1 . 3 0

1 . 2 0

i. I0

1. O0

i • A .

g

[] 1 . 101

0 1 . 200

1 . 3 0 0

1 . 4 0 0

V 1 . 4 9 9

1 . 6 0 0

i

~ - ; ~ - -, ~ , , r ~

iI

m 0 E'J

3; & 0

h,~,r

O. 9 0

-8 - 4

¢o

4 8 12


Bottom wall, solid plate Figure 7. Continued.

16 20 24 28

i. 70

S_~mbol M®

E] 1.101

0 i. 200

1. 300

<] 1.400

V 1.499

I> 1 .6oo

t~

e-~

o

1.60

1 . 5 0

1 . 4 0

1 . 3 0

1 . 2 0

I . i 0

%~'-'~ A- 7- - v ' - - v -'-,.V--~ - - v - - - V

,,-...~ 4.. ~ ~ . ~ J " ~

-!- 2 4 I . O0

0 .90 - 8 - 4 0 4 8 12


d. Bottom wall, porous plate Figure 7. Continued.

16 20 24 28 )> m

o .-i -n

Zo I,¢

C~

1 . 70

1 . 6 0

1 . 5 0

¢d

0

1 . 4 0

1.30

1 . 2 0 - - -

1. i0

1.00 - -

0 . 9 0 - -8 -4

S / n b o l M®

[ ] 1 101

O 1 200

Z~ ~ 1 300

<3 1 400

V 1 499

I> 1 600

-L>-- ~ ' ~ ~ _J -+ . . .~ . - - I , . ,~I,_ +~.+.~

0

_~.:< ..<]..~ ;_<~_, ~ ;_~_, <p-xb~--<k.~:p~l--<].~'.-~-,

Z~. ~ -Z~,-~ L - - ~ r - ~ . ~--.~-~__~-~- ^ ~

• _ '.}"E]'-[ H ] - - [ . L L : I ~ 3 - - D - t I ' E P ~ - - ~ - - L ~ ' L [ ~ P. ,J '~. - r

7

4 8 12 16 20 Tunnel Station, ft

e. T o p wa l l , po rous p la te

Figure 7. Concluded.

i|

24 28

m

65

~B

0

t~

o 4~

- r l :> OJ

,D E

2;

~)

o ~4

O. 0 3 2

0.028

O. 024

O. 020

0.016

0.012

O. 0 0 8

O. 004

Note: 20 for Station i to 20 ~ 2.0 percent i ! j o 0 C e n t e r l i n e

0 Solid Floor

Porous Floor J ~ 1 . 5 percent M Porous C e i l i n g

o *lOper, e ° t .

Relative Criteria 0

°

I I I I I I I I I 0.2 0.4 0.6 0.8 1.0 1.2 1.4 1.6 1.8

Mach Number (M®)

Figure 8. Effect of orifice selection on the Mach number deviations with X = X*, 0 = O, and Pt = 1,600 psfa.

m o o

"n & 0

A E D C - T R - 8 0 - 3 2

o 4J ¢d >

k

J= ¢) ¢d

O

0 . 0 3 6

0 . 0 3 2 -

0 . 0 2 8 - -

0 . 0 2 4 - -

0 . 0 2 0 - -

0 . 0 1 6 - -

0 . 0 1 2 _

0 . 0 0 8 --

O. 004 _

O

2.0 percent A|

O Statlons 1%o 20 # /

D Stations 3 to 19 / O

Stations 0 t o 18

/ o oeroe°, o

-.,v- 8 0

~ 0 . 5 p e r c e n t M

~ o 08o °

I I I I I I I I 0 . 2 0 . 4 0 . 6 0 . 8 1 . 0 1 . 2 1 . 4 1 . 6

Mach Number (~i®)

Figure 9. Effect of test region location on the Mach number deviations with }, = ~* , 6 = 0, and Pt = 1,600 psfa.

42

4~ t~J

0 Long P i p e

[] Shor t P i p e

f L ± I 1.~o ~ ~ ~ - - j ~,

~ ~ ~ I ~ I o

¢ ~ , - . - ~ t ,

i.lo ~ r ~ V- ~'~ - - ~ ~ - - - ~ " - ~ .......... ~" '

1. O0

0 . 9 0 -8

! -4

Figure 10.

0 4 8 12 16 20 24 Tunnel Station, ft

Effect of centerline pipe length on the Mach number distr ibut ions from M = 1.1 to 1.6 wi th )~ = ;k*, 0 = O, and Pt = 1,600 psfa.

28

~> m 0

J4 -11

do o

J~

O. 032

0 . 0 2 8

0 . 0 2 4

o o.020

>

O.Ot6

s

z

0.012

O. 0 0 8

0. 004

0

0 S h o r t P i p e

Long P i p e

I 0 . 2

Figure 11.

1 . 5 p e r c e n t M o

0

D e v i a t i o n s f o r T u n n e l p e r c e n t M Stations 6 t o 18

7A A Relative Criteria f o r " G o o d " .'da(:h 8 N u m b e r Distributions

0 a

o A

I I I I i i I I 0 . 4 0 . 6 0.8 1.0 I .2 1.4 1 . 6 1.8

Math Number (%{)

Effect of centerline pipe length on the Mach number deviations with ;k = ;k*, 0 = O, and Pt = 1,600 psfa.

m ¢9 0

- n

d0 0

I%)

t~

o

0J

E

k~ .c u

D cq

0 . 0 3 2

0.028

0.024

0 . 0 2 0

0 . 0 1 6

O. 012

O. 008

O. 004

0

2 . 0 p e r c e n t M m

Re£. 4

1 . 5 p e r c e n t M B

D e v i a t i o n s r o t T u n n e l Stations 6 to 18

_ percent Ms

Relative Criteria _~ _/~/

//y/o

_ ~ - ~ ' ~ ' / / 0 . 5 p e r c e n t M®

I I I l I I I I J 0.2 0.4 0.6 0.8 1.0 1.2 1.4 1.6 1.8

Mach Humber (M)

Figure 12. E f ~ of Macb number on the cenmrline Mach number dev ia t ionswi thk=A* ,O=O, a n d ~ = l , ~ O p s ~ .

m

3U

0

~0

o

0 0

0.70

0.60

0 . 6 0

0 . 6 0

0 . 6 0

0 . 6 0

0 . 6 0

N o t e : 2u f o r S t a t i o n s 6 t o 18

I ! = 1 . 0 9 5

2o = 0.0019

• 1- ~0 = 0 . 0 6 8

= 1.108

2u = 0.0020

~ = 0 !

I l l cJ C)

: I)

0

0.60

0 . 5 0 1 - 4 0 4

Figure 13.

8 12 16

Tunnel Station, ft

20 24 28

a. M . = 0.6 Effect of plenum chamber suction on the centerline Mach number distributions at Pt = 1,000 psfa with 0 = O.

4~

0.80

0.70

O. 7 0

0.70

z

o 0.70

~ 0 7 0 0

0.70

Note" 2 0 for Stations 6 to 1"8

I = 1.125

20 = 0.0020

= 0 . 0 5 9 l

= 1.147

2o = 0.0021

0~ = 0 I I

I l

0.70

0.60 - 4 0 4 8 12 16 2O 24

Tunnel Station, ft

b. M =0.7 Figure 13. Continued.

28

m

c)

O

M

oo

J:/ 0 d

r-4

0 0

0.85

0.75

0 . 7 5

0 . 7 5

0 . 7 5

0 . 7 5

0.75

N o t e " 2~ f o r S t a t i o n s 6 t o 18

i I . . . . X = 1 . 1 5 3

2 o = 0 . 0 0 1 8

= 0.056

..... I ! )

I

X = 1.169 b,

2o = 0.0021

m = 0

m

0 ¢3

& ¢D

0.75

0.65

-4 0 4 8 12 16 20 24

Tunnel Station, ft

c. M® = 0.75 Figure13. Concluded.

28

Note" 2c for Stations 6 to 18

0

v-4

0 0

O. 70

0 . 6 0

0 . 6 0

O. 60

0.60

O. 60

0.60

i

2~ =

~ =

i i I

1 . 0 9 7

0 . 0 0 1 7

0 . 0 2 5

I

.... A = 1.112

2a = 0.0021

~ = 0

I i 0 . 6 0

O. 50

-4 0 4 8 12 16 20 24 28

Figure 14.


a. M = 0 . 6 Effect of plenum chamber suction on the centerline Mach number distributions at Pt = 1,600 psfa with 0 = O.

m o c)

~0 & 0

(D

0.80

.C 0

O O

N o t e : 2 a f o r S t a t i o n s 6 t o 18

O. 70

I I I J I i

0.70

O. 70

O. 70

O. 70

0 . 7 0

O. 70

0 . 6 0 - 4

I I I

I

t~ 0

I I I I

i .. "~

I i I !

I J

j_

= 1.129

2G = 0.0019

= 0.023

= I. 150

2a = 0.0024

CO = 0

0 4 8 12 16 20 '24 28

m o

& 0

Tunnel Station, ft

b. M = 0 . 7 Figure 14. Continued.

t~

0.85

0.75

O. 75

0 . 7 5

o 0 . 7 5 c~

¢-4 0~ 0 7 5 0 0

0.75

0 . 7 5

Note" 2u for Stations 6 to 18

I I

I i I I

I ~ -- 0.020

~ I I l - - - ) I I ._. ~ . _ ~ . . _ ~ ~

I i

= I. 155

2~ = 0.0020

X = 1.171

2u = 0.0022

= 0

0 . 6 5

- 4 0 4 8 12 16 20 24

Tunnel Station, ft

c. M . = 0.75 Figure 14. Concluded.

28

m

o

~0 & O

bJ

t~ ~J

0.70

0 . 6 0

0.60

0 . 6 0

o 0 . 6 0

t--I

0.60 O O

0.60

0.60

0.50

Note: 2o for Stations 6 to 18

!

I

I I 2o

' I

= 1. 096

= 0. 0026

= 0. 066

= 1.118

20 = 9.O023

~ = 0

-4 0 4 8 12 16 20 24 28

Figure 15.

Tunnel Station, ft

a. M= = 0.6 Effect of plenum chamber suction on the centerline Mach number distributions at Pt = 2,200 psfa with 8 = O.

> m

o

Do & 0

r,.I

t~

0.80

O. 70

0 . 7 0

O. 70

~C u O. 70

r-~

0 70 U 0

O. 70

O. 70

N o t e " 2o f o r S t a t i o n s 6 t o 18

k = 1.130

2a = 0.0022

= 0.062

~ " ~ ' ~ " ":" " ~ " ~- 'x,:~x~Z~ ~ -

. . . . . . . . . . . ~ , . 2 ~ . ~ . . . .

k -- 1. 157

2a = 0.0024

~ = 0

I

0 . 6 0 - 4 0 4 8 12 16


b. M. = 0.7 Figure 15. Continued.

20 24 28

m o c)

"n & 0

~J

0.85

Note:

0.75

0 . 7 5

¢D

O. 7 5

Z

o O. 7 5 c~

r"q

0 . 7 5 o 0

O. 75

O. 75

O. 65

-4

20 for Stations 6 to 18

= 1.156

2o = 0.0022

t~ 4~

= 0 . 0 5 9

..... I ............. l___i I

)t = 1 . 1 8 1

2o = 0.0024

~ = 0

I I I

0 4 8 12 16 20 24 28

Tunnel Station, ft

c. M® = 0.75 Figure 15. Concluded.

m

o

~o

0

0 . 0 6 0

0. 050

0 .040

Mach Number

0 0 .6

[] 0 . 7

A O. 75

F l a g Denotes No S u c t i o n

0

[]

0 1 Pt

I I

z~

= 2,200 p s t a

I I

A E D C-TR-80-32

c

v

0 4 ~

k

0

0 . 0 6 0

0.050

O. 040

0

0

Z~

[]

0(~ Pt = 1,600 psfa

I I I I I

0.070

0 .060

0 .050

0 B

O 0

f

O A

A

A

c f cff

Pt = 1 , 0 0 0 p s f a

0.040 I I I I I 1 . 0 8 1 . 1 0 1 . 1 2 1 . 1 4 1 . 1 6 1 . 1 8

Tunnel P r e s s u r e R a t i o ,

Figure 16. Effect of tunnel pressure ratio on the total power factor at M= < 0.75 with 8 = 0.

55

O. 70

S y m b o l SH x 10 + 3

E] 4 . 367

O 7 . 310

m o

-4

o

0 . 6 0

Cr~

0 . 6 0

0.60

z

0.60 al

i - - I 0 . 6 0

o o

O. 60

I I l i

0.60

0 . 5 0

- 4 0 4 8 12 16 20 24


28

Figure 17. a. M= -- 0.6, Pt = 3,200 psfa

Effect of test section humidi ty on the Mach number distributions wi th ;~ = ~* and 8 = O.

1 . 0 0

0 . 9 0

0 . 9 0

0 . 9 0

o 0 . 9 0

O. 90 o 0

0 . 9 0

0 . 9 0

0 . 8 0

- 4 4

Symbol SH x I0 + 3

0 0.583

0 9.089

8 12 16


b. M. = 0.9, Pt = 1,200 psfa Figure 17. Continued.

20 24 28

m 0 ¢3

& o

t ~ oo

#3

z

J~ o

P4 e~ o o

Symbol SH x I0 + 3

[] 1.610

0 6.184

1.00

0 . 9 0

O. 90

0.90

0.90

0.90

0 . 9 0

0 . 9 0

0 . 8 0

- 4

! !J I , I I I

4 . - , i , - - f

J J 0 4 8 12 16 20 24 28


m

c)

-n & 0

I0

c. M . = 0.9, P~ = 2 ,400 psfa Figure 17. Continued.

1 30

1.20

Symbol SH x 10 + 3

Q 0.529

0 2.523

t~

1.20

sl 20

o 1 20

1 20 o 0

1.20

1.20

I. i0 -4 8 12 16

Tunnel Station, ft

d. M= = 1.2, Pt = 1,600 psfa Figure 17. Continued.

20 24 28

m 0

-n

& o

1.60

Symbol SH x 10 + 3

[] 0. 767

O 5.898

m O

~0

o

1.50

0

J= o

P~

o 0

1.50

1.50

1.50

1.50

1.50

1.50

1"404 0 4 8 12

Tunnel Station, ft

e. M® = 1.5, Pt = 1,600 psfa Figure 17. Concluded.

16 20 24 28

A E DC-T R-80-32

n

E

Z ¢., o

b~

0 . 6 1

0 . 6 0

0 . 5 9

0 . 9 1

O. 9 0

0 . 8 9

0.91

O. 9 0

0.89

Maximum Permissible Specific Humidity from the Criterion is 13.1.

-~OOo o o o o % 0 0 , 00

I I I I I 4 5 6 7 8 9

SH x 10 + 3

a. M=

-~O~OoO

I 0 2

b. i= .

= 0.6, Pt = 3,200 psfa

I I 4 6

SH x I0 ~ 3

= 0.9, Pt = 1,200 psfa

Dryness Criterion --~

[ o [

f [

I il 8 10

m

czo o Oo

I 1 2

Figure 18.

Dryness Criterion --~

0 0 0 0 0 O 0 0 I

° o I

I i I

5 I I 3 4

SH x i 0 + 3

c. M= = 0.9, Pt = 2,400 psfa Effect of test section humidity on the average Mach number with X = ;k* and 8 = 0.

00000

61

A E DC-T R -80-32

v

~ v

1.21

1.20

1 . 1 9

1.50

1 . 4 9

1.48

I o°B °°° olo 0 0 0

~--- Dryness Criterion

I t L 2 3

SH x i0 + 3

d. M = 1.2, Pt = 1,600 psfa

0

O OOOoo o

0 0 0 0 0 0

0 0 I ~ - - - - - D r y n e s s C r i t e r i o n

I 2 3

SHx 10+ 3

I 4

I 4

0 0

0

I 5

I 6

0 0

e. M . = 1.5, Pt = 1,600 psfa Figure 18. Concluded.

62

A E D C-T R-80-32

=-,

0

o

.0 E

0 -,4 4~

0.,4

~ o o

0J

E

Z

¢-

.rd

4~

c~ o

0

z

0 . 0 0 4

O. 002

0

0 . 0 0 4

0 . 0 0 2

O. 004

0.002

0

0 0 0 0 0 0 OOc~

Maximum Permissible S p e c i f i c H u m i d i t y f r o m t h e C r i t e r i o n i s 1 3 . 1

I I I I 5 6 7 8

SH x i0 + 3

a. M® = 0.6, Pt = 3,200 psfa

~ O o O ~ o o O O

~ o o o

Dryness C r i t e r i o n

I o I

I I I I

I I I I I, 2 4 6 8 10

Si t x 1 0 + 3

b. M® = 0.9, Pt = 1,200 psfa

D r y n e s s C r i t e r i o n

o o o o o o o o o o I m o ~

I I I

I I I I I I 2 3 4 5 6

SH x 1 0 + 3

Figure 19. c. M . = 0.9, Pt = 2,400 psfa

Effect of test section humidity of the 20 Mach number deviations with X = X* and 8 = O,

I 1 2

63

A EDC-TR-80-32

¢- 0 .i,d +J

D

E

0

~) .r. w

[]

Z

O. 040

o.o2o

0

0 . 0 4 0

0.020

'0

- OE~ED O O

~------Dryness Criterion

I Jo O O O

r i

i I J i I 1 2 3 4

SH x i0 + 3

d. M= = 1.2, Pt = 1,600 psfa

~v------Dryness Criterion

I o l o o

0 J oOO O

O OOO COO O I

I I 1 2

0

I 5

0 0 0

I I I I 3 4 5 6

SH x 10 + 3

e. M= = 1.5, Pt = 1,600 psfa Figure 19. Concluded.

64

L 0

E

U

0 . 6 0 0

0 .598

0 .596

0 .594

0 Top Wall

Bottom Wall

0 East Wall

West Wall

0 C 0 0 O-- 0

I I I I I I I I

MNA = 0.5974

20 ~ 0.0020

0 ' I I I I i

MNA

tal

E -I

.c o

O.GO0

0 .598

0 .596

0 .594 8.

East Wall

a. Tunnel station-12

' I I I . I I 6 4 2 0 2 4

Orifice Location, ft

0 MNA = 0 . 5 9 8 6

2c = 0 . 0 0 2 8

I I i I I I I I 6 8 8 6 4 2 0 2 4

Oriftce Location, ft West Bottom Wall Wall

~[NA

I 6

Top Wall

Figure 20. b. Tunnel station -4

Nozzle wall Mach number distributions at M. = 0.6008 and M© = 0.5912 with X = X*, ~ = 0, and Pt = 1,600 psfa.

m o t-)

-n

do O

0. 7 9 6

0 . 7 9 4

E

z 0 , 7 9 2

0 . 7 9 0

0.788

0

0 Top Wall

0 Bottom Wall

East Wail

West Wall

, I I I I I I I

MNA = 0.7934

20 = 0.0039

I

A

O i i l i [

MNA

m

o

& 0 /.,

0% 0.800

0.798

S

z 0 . 7 9 6 - -

0

m 0 . 7 9 4 - -

0 . 7 9 2 8

E a s t W a l l

a. Tunnel station -12

C~

MNA = 0.7979

20 = 0.0041

m

j i 8 (' i.) 6

West Bottom Wall Wall

s S

s'~l i I l I 4 2 0 4 6 6


I I,, I I I 4 2 0 2 4


MNA

T o p Wall

Figure 21. b. Tunnel station -4

Nozzle wall Mach number distributions at Ma = 0.7996 and Mc = 0.7890 with X = k* , ~ = 0, and Pt = 1,600 psfa.

..j

(D

0

0 . 9 7 0

0 . 9 6 8

0 . 9 6 6

0 . 9 6 4

0 . 9 6 2 -

O. 9 6 0 -

O . 9 5 8 -

0 . 9 5 6 -

0 . 9 5 4

8

East Wall

I 6

I

4 2 0 2 Orifice Location,

0 T o p W a l l

Q B o t t o m W a l l

0 E a s t W a l l

W e s t W a l l ~A = 0 . 9 6 4 1

2~ = 0 . 0 0 8 9

A

0

. I I I J I I I I I 4 6 8 8 6 4 2 0 2 4

ft Orifice Location, ft West B o t t o m Wall Wall

MNA

I 8

Top Wall

Figure 22. a. Tunnel station -12

Nozzle wall Mach number distributions at Ma = 0.9979 and M© = 0.9859 with k = k* , e = 0, and Pt = 1,800 psfa.

m

o

& O

O0

0 . 9 9 6 - -

0.994 - -

~ 0.992 - -

o 0 . 9 9 0 - -

0 . 9 8 8 - -

0 . 9 8 6

8

East Wall

O Top Wall

O Bottom Wall

<> East Wall

West Wall MNA = 0.9927

~ / / ~ ~ , ~ . ~ 2~ = 0.0056

4"

,S

o cr"

I I I I I . I I , . I 6 4 2 0 2 4 6 8

O r i f i c e L o c a t i o n , f t

n..

I

6

0

"- ..~__ MNA

I I I, I I 4 2 0 2 4 Orifice L o c a t i o n , f t

West Bottom Wall Wall

I , . , [

6 8

Top Wal I

m o o

;0 & 0

b. T u n n e l s t a t i o n -4

F i g u r e 22 . C o n c l u d e d .

1 . 2 3 0 - -

1 . 2 2 5 -

1 . 2 2 0 - -

1 2 1 5 - -

1 2 1 0 - -

1 2 0 5 - -

1 2 0 0 - -

1 195 -- o

t 1 1 9 0 - -

1 . 1 8 5 --

1 . 1 8 0 - -

1 . 1 7 5 - -

1 . 1 7 0

1 . 1 6 5

8

E a s t W a l l

MNA = 1 . 2 0 8 0

2 q = 0 . 0 4 8 7

6

I I

I I

I I

I I

I I

I I

I I I "

I I

I I

I

I 4

0

0 Top Wall

O Bottom Wall

<> East Wall

West Wall

h

I I 1 i I I , ,1 I , I I l 2 0 2 4 6 8 8 6 4 2 0 2 4

Ori£icc Locatlon, ft Orifice Location, ft West Bottom Wall Wall

Figure 23 . a. T u n n e l s tat ion -12

N o z z l e wal l M a c h n u m b e r d is t r ibut ions at Ma = 1 . 2 0 2 3 and Mc = 1 . 1 8 6 8 w i t h ;~ = ;~*, 0 = 0, and Pt = 1 , 6 0 0 psfa.

MNA

I 8

T o p W a l l

~> m

o c )

-11

do o

7> m

o

~0

0

0

1.215 _

1.210 --

1.205

1 . 2 0 0 Z

0 1 . 195

1 . 1 9 0 - -

1 , 1 8 5

• 8

East Wall

0 Top W a l l

[] B o t t o m W a l l

<>East W a l l

% %

/ I

I /

/

I I I I I J 4 2 0 2 4 6

Orlf{oe Location, f¢

-- MNA - 1. 2050

20 - 0.0131

-

I I

8 8 6

West Bottom W a l l W a l l

I I I I . I 4 2 0 2 4

Orlflce Location, ft


! I 6 8

Top Wall

..j

1.425

1.420

1 . 4 1 5

1.410

~ 1.405

1 . 4 0 0

1.395

1 . 3 9 0

O Top Wall [] Bottom Wall MNA ffi 1.4052

I O East Wall 2o = 0.0188

0 i i est wall /

C \ \ /

I 8 6 4 2 0 2 4 6 8 8 6

Orifice Location, ft East West Bottom Wall Wall Wall

Figure 24.

0 A

I I I I I 4 2 0 2 4


a. Tunnel station -12 Nozzle wall Mach number distributions at M, = 1.3994 and Mc = 1.3853 with ~ = ;~*, 0 = O, and Pt = 1,600 psfa.

MNA

I I 6 8

Top Wall

m

J~ ~o & 0

--3

1.405 --

1.400 --

1.395 -- ~ o Z

~ ~ ~ 1"39° i 1.385

1 . 3 8 0 I

8 6

East Wall

O Top Wal]

O Bottom Wall

<> East Wall

West Wall

O O

P

MNA = 1.3905

2o = 0.0126

/ /

o.. /

4 2 0 2 4 6 8

OrJfice Location, ft West Wall

m

\\ - \ ,~ ...---~

8 fi 4 2 0 2 4 6 8

Orifice Location, f t Bottom Top Wall Wall


m cJ c)

3o & O

- -3

1 . 6 2 0

1 . 6 1 5

1 . 6 1 0

1 . 6 0 5

1 . 6 0 0 - -

1 . 5 9 5 - -

I . 5 9 0 - - N

I . 5 8 5 - -

I . 5 8 0 - -

1 . 5 7 5 --

1 . 5 7 0 - -

1 . 5 6 5

8

O T o p W a l l

[] B o t t o m W a l l

O E a s t W a l l

W e s t W a l l

E a s t W a l l

J

/

I I I I 4 2 0 2

O r i f i c e L o c a t i o n ,

~ A - 1 5 9 o s

2 o - 0 . 0 4 6 9

f t

Zl

Figure 25.

0

m

l I i 1 I L J 4 6 8 8 6 4 2 0 2

O r i f i c e L o c a t i o n , W e s t B o t t o m W a l l W a l l

a. Tunnel station -12 Nozzle wall Mach number distributions at M. = 1 .5985 and M© = 1 .5847 with ;~ = ;~*, 8 = 0, and Pt = 1,600 psfa.

f t

~ A

I 8

T o p W a l l m

o c)

-i1 ~0 O

r~

1 . 6 1 0 -

1 . 6 0 5 -

1 . 6 0 0 -

k

1 . 5 9 5 -

1 . 5 9 0

J 1 . 5 8 5 -

1 . 5 8 0 -

1 . 5 7 5 8

E a s t W a l l

MNA ~ 1 . 5 8 9 2

0 . 0 2 1 5

/ o " s

/ /

/ /

/

o/

I

6

l I I I I 4 2 0 2 4 O r i f i c e L o c a t i o n , f t

I J 6 8

West

Wall

0 Top W a l l

0 B o t t o m W a l l

~) E a s t W a l l

A W e s t W a l l

~A

8 6 4 2 0 2 4 6 8 O r i f i c e L o c a t i o n , f t

B o t t o m Top W a l l W a l l


m 0 f~

DO & o

0.024 -

-.3

0. 020

0.016

¢J

' 0 . 0 1 2 t~

0 , 0 0 8

0 . 0 0 4

0

0 . 4

0

0

F l a g D e n o t e s Long P i p e D a t a

I I I I I I 0 . 6 0 . 8 1 . 0 1 . 2 1 . 4 1 . 6

E q u i v a l e n t P lenum Chamber Mach Number (Me)

Figure 26. Tunnel 16T Mach number calibration w i th X = ;k*, 6 = O, and Pt = 1,600 psfa.

J 1 . 8

m [3 t'~

~0 & o

r~

o~

- 0 . 0 1 0 - -

- 0 . 008

- 0 . 006

, ~

- 0 . 004

- 0 , 0 0 2

0

0

8

Z M

S u p e r s o n i c

0 O.,.Mo °

= 1 , 4

= 1 . 2

0 0

S u b s o n l c

Moo = 1 . O

Oo o ~ 0 /

L Moo = 0 . 8

- 1 . 6

0 . 1 0 . 2 0.3 0 .4 0 . 5 0 .6 0 .7

P c / P t

0

~----M~ ~ 0 .6

0 . 8

3> m

-11

do 0

N)

a. Test section and plenum static pressure difference Figure 27. Tunnel 16T pressure calibrations from M® = 0.6 to 1,6

with k = ;~*, 0 = O, and Pt = 1,600 psfa.

0 . ~ B

0 M® = o.6o

,.,j

0 . 7

0 . 6

.I.J

0 . 5

0,4 m

.0.3 --

0 . 2

0 . 2

0

0

0

0

0

0 M= = 1.00

0

0

0

0 M= = 1.40

0

M= = 1 . 6 0

I I 0 . 3 0 . 4

M= = 1.20

I I 0 . 5 0 . 6

Pc/Pt

b. Test section static pressure only Figure 27. Continued.

0

0

Moo = O. 8 0

I I 0 . 7 0 . 8

m

o

-11 do 0

! 0

A E DC-TR-80-32

-0,008

-0,006

i - 0 .004

-0 .002

0

0 .002

Supersonic Subsonic

• 0 M®= 1 .o - o - - ~ = 1 . 4 /

°o ~ ° s M~ =1.6 0 0 ~/ - 0 y ~ = 1 . 2 O

I i O i I I I Pn_4/Pt

c. Test section and nozzle static pressure difference at station -4

-0 .024

-0,020

-0,016

[ -0 .012

¢k

~ - 0 . 0 0 8

m

M

S u p e r s o n i c

= 1 . 6

-0,004

Subsonic

M = 1,0

0

0 0

•Z/•, ° °

M = 0 .8 o - O M

i.~4--" m/'Mc° = 1.2

0 . o o 4 I [2~ l I I | 0.2 0.3 0,4 0.5 0,6 0,7 0,8

Pn_12/Pt

d. Test section and nozzle static pressure difference at station -12 Figure 27. Concluded.

= 0 . 6

= 0 . 6

78

,.,j I ~1

I od

- 0 . 0 0 8

- 0 . 0 0 6

- 0 . 0 0 4

-0.002 --

0 --

0 . 0 0 2 0 . 2

O Nominal

O Jack I Moved -0.25 in.

G~ A Jack 2 Moved -0.26 in. and Jack 4 -0.I0 in.

I I I I I I 0 . 3 0 . 4 0 . 5 0 . 6 0 . 7 0 . 8

Pn_4/Pt

Figure 28. Effect of nozzle jack perturbations on the nozzle-test section calibration with ;~ = ;~*, 0 = O, and Pt = 1 ,600 psfa.

m O O

-n

do o

A E D C - T R - 8 0 - 3 2

2 , 4

qq m

,la

k 0 O

Figure 29.

2 . 3

2 . 2

2 . 1 -

2 . 0 -

1 . 9 -

Ma - Mc ~ (Pa - P c ) / P t

. . . . . P a / P t

x . s n I I I I I I 0 . 4 0 . 6 0 . 8 I o 0 1 . 2 1 . 4 1 . 6 1 . 8

Mach Number ( M )

a. Pt = 1,000 psfa Effect of the calibration method on the uncertainty of the calibrated free-stream static pressure with e = O,

80

A E D C - T R - 8 0 - 3 2

2 . 6 w

2 . 5 -

2 . 4 -

q~

: ' 2 . 3 - -

,IJ

o 2 . 2 - - ;::)

2 . 1 -

. . . . p a / P t

I

2 . 0 - - •

z . 9 I I I I I I I 0 . 4 0 . 6 0 . 8 1 . 0 1 . 2 1 . 4 1 . 6 1 . 8

M a c h N u m b e r ( ~ )

b. Pt = 1,600 psfa Figure 29. Continued.

81

AEDC-TR-80-32

2 . 8 , -

2 . 7 B

2 , 6 -

2 . 5 -

4~

~ 2 . 4 -

2 . 3 -

2 . 2 - -

2 . 1 I 0 . 4 0 . 6

~ M a - M c

~ ~ ( P a - P c ) / P t

. . . . P a / P t

\

/

I i I I I I 0 . 8 1 . 0 1 . 2 1 . 4 1 . 6 1 , 8

M a c h N u m b e r ( M )

c. Pz = 2,500 psfa Figure 29. Concluded.

82

A E DC-T R-80-32

0 . 0 0 7 -

0 . 0 0 6 -

0 . 0 0 5 - 4~

0

0 . 0 0 4 -

0 . 0 0 3 [

0 . 4

Figure 30.

- - M - M a c

~ ( P a - P c ) / P t

. . . . p a / P t

/ /

/ /

I I

I I

/ /

I I I I I I I I I I I 0 . 6 0 . 8 1 . 0 1 . 2 1 . 4 1 . 6

Mach Number ( M )

a. Pt = 1,000 psfa Effect of the calibration method on the uncertainty of the calibrated free-stream Mach number with 0 = O.

83

A E DC-T R -80-32

:~8

4..)

-,-4 ¢d

0

0.005 -

0 . 0 0 4 -

0 , 0 0 3 --

i I 0 . 0 0 2 0 . 4 0 . 6

--M a - M c

~ - - - (Pa - Pc) /P t

P a / P t

I I I I I I I I I I 0.8 1.0 1.2 1.4 1.6

Mach Number (M)

b. Pt = 1,600 psfa Figure 30. Continued.

84

A EDC-TR-80-32

8

-u - I

t .

r . ) e~

0 . 0 0 3 - -

0 . 0 0 2 - -

i

0 . 0 0 1 0 . 4

iI ~ M - M a c

( P a - P c ) / P t

. . . . p a / P t • /~/

I I I I I I I I I I I 0 . 6 0 . 8 1 . 0 1 . 2 1 . 4 1 . 6

Mach Number (M=)

c. Pt = 2,500 psfa Figure 30. Concluded.

85

o o

0

I

0 . 0 2 0

0 . 0 1 6

0 . 0 1 2

0 . 0 0 8 m

0 . 0 0 4

0

0 . 4

R e f .

0 . 6

Figure 31.

4 C a l i b r a t i o n

0

O 0

F l a g D e n o t e s Long P i p e D a t a

§

0 . 8 1 . 0 1 . 2 1 . 4 1 . 6

Mach Number ( M )

,

Effect of Mach number on the calibration with ;~ = k*, e = O, and Pt = 1,600 psfa.

1 . 8

m o

:t "n

0

oo

0

I

0.020

0 . 0 1 6

0.012

0 . 0 0 8 - -

O. 0 0 4 --

0 0 . 4

Zl

I 0 . 6

Figure 32.

0 S h o r t P i p e .

A L o n g P i p e

~ ~ 6 ~ ~ ~ " 0 lit o8

I , 1 | 0.8 1.0 1.2

Mach N u m b e r (Moo)

Effect of the centerline pipe length on the calibration with X = ;~*, 0 -- O, and Pt = 1,600 psfa.

I I 1 . 4 1 . 6

3> • m

c~ c) J~ DO & 0

00 Oo

O

I

0 . 0 2 0

0.01~

0.912

0.008 --

0.004 --

0

0.4

O S h o r t P i o e

Long P i p e

F l a g D e n o t e s P l e n u m Suction Not Used (~

08 tff 8°°°

A

I . I I I I I 0 . 6 0 . 8 1 . 0 1 . 2 1 . 4 1 . 6

Nach Number (M=)

I 1 . 8

m

o

r~

Figure 33. Effect of plenum chamber suction on the calibration at M ~ 0.75 with ;~ = ;~*, 6 = O, and Pt = 1,600 psfa.

A E DC-TR-80-32

0 . 0 1 4 --

I

(d

~..

I

0.012

0 . 0 1 0

0 . 0 1 2

0.0]0

0.008

0~00 0 0 0 0 00~

Maximum P e r m i s s i b l e Specific Humidity from the Criterion is 13.1

I I I J 6 7 8 9

SH x 10 + 3

a. M® = 0,6, P,

- ~ ° o o % ~ o o o O

I I I 2 4 6

= 3,200 psfa

D r y n e s s C r i t e r i o n

o I I I I

I II 8 10

S H x 1 0 + 3

Figure 34. b. M = 0.9, Pt = 1,200 psfa

Effect of test section humidity'on the Mach number calibration with ~ = ;~*, ~ = O.

89

A E DC-TR-80-32

0

i

X

I

aS

0.014

0 . 0 1 2

0 . 0 1 0

0 . 0 1 6

0 . 0 1 4

0.012

% o 0 o o

Dryness Criterion - - - ~

I 0 0 0 0 0 0 o ° 0 0 I

I I I

I I I I 3 4 5

SH x 10 +3

c. M. = 0.9, Pt = 2,400 psfa

iO•--oDryness Criterion o o O°Oo

I 0

I I

I J I I I 1 2 3 4

SH × 10 +3

d. M. = 1,2, Pt = 1,600 psfa Figure 34. Continued.

0 0 ~ o

I 6

90

A E DC-T R -80-32

0.016 -

0.014

0.012

0.010

o

i 0.008 o~

0.006

O. 004

0.002 --

0 0

O O~/~-Dryness

OO O

I I o

0

Criterion

O

O O

O

I I 2 3

SHx I0+ 3

e. M, = 1.5, Pt = 1,600 psfa Figure 34. Concluded.

O

O

I 5

O

° I 6

9]

=. A E D C - T R - 8 0 - 3 2

APPENDIX A NOZZLE JACK PERTURBATIONS

The Tunnel 16T nozzle design contours were modified by utilizing off-design contours or

by perturbing various combinations of nozzle jacks 1, 2, 4, 5, and 6 to improve the

centedine Mach number distributions. The disturbance at tunnel station 4 at M~ = 1.2

reported in Ref. 4 was a special concern, especially since it had become larger (Fig. 7a) and

extended to tunnel station 8. Since extending the calibration pipe did not remove the

disturbance, a nozzle irregularity was assumed to cause the disturbance. The effects of

perturbing the nozzle on the Mach distributions at Moo = 1.2 are presented in Fig. A1. The

disturbance at tunnel station 4 was not removed, but the flow acceleration at tunnel station 5

was decreased. In general, the Mach number distribution was improved and the 2a

deviations decreased as the nozzle was perturbed. The fact that the nozzle perturbations did

not remove the disturbance at station 4 reinforces the possibility of the disturbance

originating at the test section-nozzle interface (STATION 0), as indicated by Mach lines

traced from tunnel station 0 which intersect the calibration pipe in the vicinity of tunnel

station 4 presented in Ref. 4. This hypothesis should be investigated during a subsequent calibration.

The effects of the nozzle perturbations at M® = 1.0, 1.3, 1.4, 1.5, and 1.6 are presented in Figs. A2 through A6. The Mach number distributions were also improved at M_ = 1.4,

1.5, and 1.6. The Mach number distributions were not changed at M® = 1.0 and became

worse at Moo = 1.3. The disturbances in the Mach distributions downstream of tunnel

station 16 were not affected by changes in the nozzle contours. These disturbances may be

attributed to surface irregularities on the calibration pipe, orifice imperfection, or waves originating test section walls.

The data presented in Fig. A7 show the perturbations that had the most influence in

making the calibration parameter ( M a m Me) equal the Ref. 4 data. The other perturbations

had a smaller influence on the calibration or increased the difference between the current and Ref. 4 data. This indicates the possibility that the nozzle has changed between the current and Ref. 4 calibration test.

The data presented in Figs. A1 through A6 indicate that the centerline Mach distributions can be improved and the 20 deviations reduced. As a result of these data and

nozzle contour measurements which indicated some nozzle jacks were out o f tolerance, the

nozzle and nozzle positioning system are being investigated. Additional discussion is beyond the scope of this report.

93

~D 4~

40

35

1 30

k

~ I 25

~1 20

m

~i 15 o ,-3

1. i0

1.05

1.00

Symbol M® TPR WAA Re x 10 -6

O 1.200 1.261 0.00 3.257

D 1.200 1.260 0.0O 3.261

1 . 1 9 9 1 . 2 6 0 0 . 0 0 3 . 2 6 2

1.201 1.260 0.00 3.260

PT 20

1599 0.0201 NCN 14

1600 0.0145 NCN 13

1601 0.0122 NCN 13,

1600 0.0120 NCN 13,

J1 (-0.12)

J1(-0.25)

!

- 8

, I

I . - - - t

b - - - ! I

[ , 1

,L P- , , i ~

~ _" - . - - 4

I

- 4

i I

- - !

- - I

- - . !

0

Note:

I

I - -

I

I

I


I --

4- -- -'--

- - q

- - I I

I 1 - - - -

I ]

I I

! I -

, [_- i

!

- - I i 20 24

I I

i

I I . . . . .

I I

i . ,

8 12

T u n n e l S t a t i o n ,

16

It

Figure A-1. a. Contour 13, jack no. 1

Effects of nozzle jack perturbations on the centerline distributions at M® = 1.2.

28

)> m

c}

"n

& O

1.40

Symbol __M= --TPR __WAA Re x 10 -6 PT 20

O 1.201 1.258 0.0 3.262 1599 0.0210 NCN 14

[] 1.200 1.260 0.0 3.257 1597 0.0137 NCN 14, Ji(-0.25)

1.200 1.260 0.0 3.259 1599 0.0131 NCN 14, JI(-0.35)

N o t e : 2a f o r S t a t l o n s 6 t o 18

1.35

1.30

g 1 . 2 5 Z

~ 1 . 2 0

~ 1 . 1 5 0

1 . 1 0

1.05

1.00 -8 -4 0 4 8 12 16 20 24

Tunnel Station, ft

b. Contour 14, jack no. 1 Figure A-1. Continued.

28

~> m

o

& o

Symbol .

0 1 . 2 0 1 1. 258 0 . 0

[3 1. 201 1 . 2 6 0 0 . 0

1 . 2 0 0 1 . 2 5 9 0 . 0

N o t e : 1 . 4 0

M~ TPR WAA Re x 10 -6 PT 2u

3.262 1599 0.0210 NCN 14

3.261 1599 0.0141 NCN 14, J4(-0.10)

3.265 1602 0.0122 NCN 14, J4(-0.10), J2(-0.26)

2u for Stations 6 to 18

m

o

C)

1.35

O~

1 . 3 0

Q)

~ 1 . 2 5

"~ 1 . 2 0 - -

1.15

I.I0

1.05

/

" - ' ~ - - ~ , ~ , ~ o ~ ~ - '-~ - - - '

I. 00 -8 -4 0 4 8 12


16 20 24 28

c. Contour 14, jack nos. 2 and 4 Figure A-1. Concluded.

1.20

Symbol

0 []

M= TPR WAA Re x 10 -6 PT 20

0.999 1.220 0.00 3.183 1601 0.0031 NCN 1

0.999 1.220 0.00 3.181 1602 0.0032 NCN I, Ji(-0.25)

Note: 20 for Stations 6 to 18

1.15 ----

%0 ..j

I.I0

0J 1.05

1.00

¢~ 0 . 9 5 ¢J o ,-1

0.85

0 . 8 0 - 8 -4 0 4 8 12 16 20

Tunnel Station, ft

Figure A-2. Effect of perturbing nozzle jack no. 1 on the centerline distribution at M= = 1.0.

24 28

m o o

~0 do O

~J

Symbol M® TPR WAA Re x 10 -6

O i. 300 1. 281 0.0 3. 253

Q 1. 300 I. 281 O. 0 3. 253

1.300 1. 281 0.0 3. 253

1.300 1.281 0.0 3.252

Note:

PT 2u

1601 0.0113 NCN 20

1600 0.0123 NCN 20, J6(-0.27)

1600 0.0113 NCN 20, J6(-0.27), J5(-0.25)

1599 0.0126 NCN 20, J6(-0.27), 05(-0.25),


i. 50 ""

Ji(-0.25)

m o

~n

& O

bO

~O OO

1.45

1.40 -

~1.35

~ 1 . 2 5 - o

1.20

1.15

1.10 -8 -4 0 4 8 12 16 20 24

Tunnel Station, ft

a. Contour 20, jack nos. 1, 5, 6 Effects of nozzle jack perturbations on the centerline distributions at M = 1.3.

¢m

Figure A-3.

28

~o

1 . 5 0

1.45

1 .dO

o

"~ 1 . 3 5

e~ 1 . 3 0

r-4

~ 1 . 2 5 o

i. 20

1.15

1.10 -8

Symbol

0

D

b

-4

M=

1.300

1.300

Note:

TPR WAA Re x 10 -6

1.281 0.0 3.253

1.280 0.0 3.260

2a f o r S t a t i o n s 6 t o 18

4 8 12 16


b. Contours 19 and 20 Figure A-3. Continued.

PT 2a

1601 0.0113 NCN 20

1603 0.0131 NCN 19

20 24 28

m

c)

-n

(D

0 0

Symbol

0

0

M= TPR WAA Re x 10 -6

1.300 1.281 0.0 3.252

1.300 1.283 0.0 3.252

1.300 1.283 0.0 3.251

Note:

PT 2u

1600 0.0117 NCN 20

1601 0.0131 NCN 20, J6(+0.25)

1599 0.0131 NCN 20, J6(+0.25), J1(-0.25)

2u for Stations 6 to 18

I. 50

1.45

1.40

1.35 ----

o I. 30 ~u

= 1.25 o o

1.20

[ 3 - ~ - ~ - , ~ I

m o (~

-n

O

~J

1.15 - -

I.I0

-8 - 4 0 4 8 12 16

Tunnol Station, ft

c. Contour 20, jack nos. 1 and 6 Figure A-3. Continued.

20 24 28

Symbol _M= TPR WAA Re x 10 -6 PT ___.2~___

O 1.300 1.281 0.0 3.252 1600 0.0117 NCN 20

O 1.300 1.275 0.0 3.255 1601 0.0141 NCN 18

Note: 20 /or Stations 6 to 18

m

CD v--

1.50

1.45

1.40 -- -

1.35

-V- o

1.25 o o

1.20

1.15

1.10

-8 -4 0 4 8 12 16 20 24

Tunnel Station, ft

d. Contours 18 and 20 Figure A-3. Concluded.

28

m

o o

-n

O

1.60

1.55

Symbol

0

[]

M® TPR WAA Re x 10 -6 PT 20

1.400 1.329 0.0

1.400 1.330 0.0

N o t e :

3.217 1602 0.0162 NCN 30

3.215 1601 0.0150 NCN 30,

2o for Stations 6 to 18

J 1 ( - o . 2 5 )

m [J o

:0 & O

t~

O

1.50

"~ 1 . 4 5

u 1 . 4 0

1.35 o o

1.30

•

1.25

1.20

-8 - 4 0 4 8 12 16 20 24 28

Figure A-4.


a. Contour 30, jack no. 1 Effects of nozzle jack perturbations on the centerline distributions at M® = 1.4.

Symbol M~ TPR WAA Re x 10 -6

O 1.401 1.329 0.0 3.211

[] 1.399 1.329 0.0 3.212

1.400 1.330 0.0 3.215

PT 2o

1600 0.0165 NCN 30

1600 0.0156 NCN 30, J1(-0.25)

1601 0.0141 NCN 30, J1(-0.25), J2(-0.20)


1.60

1.55

m

1.50

1.45 E

Z

1.40

r-1

1.35 o

1.30

1.25

1.20

-8 -4 0 4 8 12

Tunnel Station, ft

b. Contour 30, jack nos. 1 and 2 Figure A-4. Continued.

16 20 24 28

rn

[3 (3

& O

1 .60

1.55

Symbol

0

Q

M® TPR WAA Re x 10 -6 PT 2o

1.401 1.329 0.0 3.211 1600 0.0165 NCN 30

1.400 1.331 0.0 3.219 1603 0.0235 NCN 33


m o c5

"11

& O

~J

4~

~2

z

o oJ

,-'4

O O

1.50

1.45

1.40

1.35

1.30

d

1 . 2 5

1.20

-8 - 4 4 8 12

T u n n e ] S t a t i o n , f t

c. Contom:s 30 and 33 Figure A-4. Concluded.

16 20 24 28

1.70

SymboI M___~a_ - TPR WAA Re x 10 -6 PT 2o

O 1.499 1.411 0.0 3.148 1600 0.0288 NCN 40

[] 1.500 1.411 0.0 3.149 1600 0.0286 NCN 40,

Note: 20 for Stations 6 to 18

JI(-0.25)

CD t~

03 J3

J3

o~ O O

1.65

1.60

i. 55

1.50

1.45

1.40

t

1.35

1.30

-8 -4

Figure A-5.

0 4 8 12 16 2O

Tunnel Station, ft

Effect of pe~urbing nozzle jack no. 1 on the centerline distr ibution at M = 1.5.

24 28

~> m

~0

O

~J

1.80

Symbol 'M® TPR WAA Re x 10 -6

O []

1.600 1.411 0.0 3.075

1.599 1.411 0.0 3.073

PT 2o

1603 0.0319 NCN 45

1603 0.0302 NCN 45, J1(-0.25)

N o t e : 2a f o r S t a t i o n s 6 t o 18

m

~0 & o

t~

Q O~

i. 75

i. 70

"~ 1 . 6 5

o .

I. 60

r-d

1.55 ¢) o

I. 50

1.45

1.40

-8 -4 0 4 8 12 16 20

Tunnel Station, ft

Figure A-6. Effect of pe~urbing nozzle jack no. 1 on the centerline distribution at M = 1.6.

24 28

O -.3

0. 020 --

0.016 --

o 0.012 --

I

0 . 0 0 8 -

0 . 0 0 4 -

0

0 . 4

F l a g D e n o t e s L o n g P i p e D a t a

0 O

I 0.6

O Nominal Contour Data

<> Jack No. 1 Moved 0.25 in. Out Using Off Design Contour 13 or Jack No. 4 Moved 0.i0 in. Out Using Design Contour 14.

[] Jack No. 8 Moved 0.25 in. in Using the Design Contour 20

I I I I 0.8 1.0 I~2 1.4

§

I 1 . 6

Mach Number (Mm)

Figure A-7. The effect of nozzle jack perturbations on the calibration with ;~ = ;~*, 0 = 0, and Pt = 1 ,600 psfa.

I 1.8

m

O

~0 & O

~J

AEDC-TR-80-32

Et

Ji

Ma

i c

Mlocal

MNA

M®

NCN

Pa

Pc

Pnozzle

Pt

P...

SH x 10+3

0

0*

k

NOMENCLATURE

Tunnel total power factor, (total power)/Pt, MW/psf

Distance nozzle jack number i is moved in in., (positive is toward the nozzle centerline)

Average Mach number from tunnel stations 6 to 18 on the centerline (Ma ~ M=)

Equivalent plenum chamber Mach number, f(P¢/Pt)

Mach number calculated at each pressure orifice using isentropic relations

Average nozzle Mach number at tunnel station -4 or -i 2

Free-stream Mach number

Nozzle contour number

Average static pressure from tunnel stations 6 to 18 on the centerline (Pa ~ P=), psf

Plenum chamber pressure, psfa

Nozzle average static pressure measured by orifices on the nozzle walls, psf

Tunnel stagnation pressure, psfa

Free-stream static pressure, psf

Test section specific humidity, Ib H20/lb dry air

Test section wall angle, deg (positive when walls are divepged)

Optimum wall angle, deg (Fig. 4)

Tunnel pressure ratio, ratio of Pt to the compressor inlet pressure

!08

A E DC-TR -80-32

k*

O"

~0

Nominal tunnel pressure ratio (Fig. 5)

Standard deviation (conventional statistical parameter)

Plenum weight flow ratio; plenum weight flow divided by the tunnel weight flow

109

supplemental calibration of the aedc-pwt 16-ft ... - dtic

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