N8 9 - 16 75 3. ,! ,t

VON KARMAN INSTITUTE FOR FLUID DYNAMICS

LECTURE SERIES 1988-04

INTAKEAERODYNAMICS

FEBRUARY22- 26,1988

CFD APPLICATION TO SUBSONIC INLET AIRFRAME INTEGRATION

Bernhard H. Anderson

NASA-Lewis Research Center, Ohio, USA

1989007377-179

https://ntrs.nasa.gov/search.jsp?R=19890007382 2020-06-19T19:48:17+00:00Z

/

'I

III III ,, .........

1989007377-183

1989007377-1_'

1989007377-185

1989007377-186

. CIRCULAR90 DEGREEINPLANEBEND :R/r = 3.2, TurbulentFlow,Roy= 40,000

StreomwiseVelocity '_: Experiment I'_

,4" Anolysis ( PNS Solution I-Meoh = 50x50x86 _ J (X

-Mesh= 25x25x86 ! "_ " I 'k_

- ! i!i "i

• Flow

Surface Sheor Stress

1989007377-187

1989007377-189

,, CIRCULAR180 DEGREEINPLANEBEND ':R/r - 7, LominarFlow,Rey- 242

PNSSolution,SecondoryFlowTheta- 50.0 degrees

[;-;-;....-,...:_1_i'

l_'

_ Analysis Experiment'

CIRCULAR180 DECREEINPLANEBENDR/r = 7, LominarFlow,Rey- 242

PN$Solution,SecondoryFlow ,:,.

i Theto- 75.0 degrees

!_ _.......-s--:,

Z.:.... :.L._--""- - - 'ORIGINALPAGEISOF POORQUALITY

Analysis Experiment (_

1989007377-191

CIRCULAR180 DEGREEiNPLANEBEND• R/r -- 7, LaminarFlow,Rey= 242• PNSSolution,SecondaryFlow

' Theta= 105.0degrees

:., _'_

_ .[2 .........

Li-_--

_ ' AnaJysis Experimento.

iCIRCULAR180 DEGREE:INPLANE.BENDR/r = 7, LominorFlow,Rey- 242 .........

PNSSolution,Seconda:,ryFlow

Theta= 1,35.0degrees ._.-!

:i_: .....

Analysis ' Experiment

1989007377-192

ORIGINALP,EC,E iS ,45OF POOR QUALITY

CIRCULAR22.5- 22.5 DEGREEINPLANES-BEND iLorninorFlow,Rey= 790

- StreQmwiseVelocity

ExperimentAnoiysis( PNSSolution)' Mesh = 40x40x80

..... Mesh = 20 x 20 x 80-

1,

\

\

%

@ ',Row ' "" +

. ('

!t

:CIRCULAR22:5- 22.5 DEGREEINPLANES-BEND ',LominorFlow,Rey = 790 \

SecondaryVelocity

• -------- 1989007377-194

" CIRCULAR22.5- 22.5 DEGREEINPLANES-BENDTurbulentFlow,Rey=-48,000

- _ StreamwiseVelocity

• Experiment'm . : Analysis( PNSSolution)

.- o Mesh= 50x 50x 80- , ..... Mesh= 25x25x80,e

•" IDI

.

I I'!

" " ' 1989007377-195

-,J7 ,'i

-4.......!3ORiGI[i;_,LP,,::...OF POORQUALITY

,,_

®

1989007377-197

,,' CIRCULAR45- 45 DEGREEINPLANES-BEND 'PNSSolution,SurfaceSkinFriction

' TurbulentFlow,.Rey= 5.0x 105

i

,.. _ o Experi.mentCF - Analysisi

., I I ,,, I , I , I

. ' S- Length

CF . r,,- 'o _o o -oI

, I I ,, I . I., I I .l

N- Length E- Length.i I; t

I

CIRCULAR45- 45 DEGREEINPLANES-BEND tPNSSolution,CompressorFaceStation

TurbulentFlow,Rey= 5.0x 105, Mesh= 50 X50X100= 2.5x 105i

f

"i Experiment 'Analysis

II.. _"..7._lt(4:!.JJ.A_Jl ,..,,jL,,_ :i

'TotalPressureLoss SecondaryVelocity

• . 1989007377_19_8

1989007377-200

•i _,. |

UNIVERSITYOFTENNESSEEINLETDUCTCirculor30-,30 degreeInp!oneS-Bend i_ . TotolPressureContours

• Aexit/Ainlet= 1.0

Experiment .Anolysis Experiment .Anolysis ,_,Theta= 45.0 degrees Theto= 60.Coegrees

UNIVERSITYOFTENNESSEEINLETDUCT..Circulor,30-,30degreeInplaneS-Bend i:

TotalPressureContoursAexit/Ainlet= 1.0 _'

_ .

Experiment Analysis Experiment AnalysisTheta= I,.5.0degrees Theto= 32.0 degrees "_

1989007377-201

........................................................................................................1989007377-202

w

®

1989007377-203

1989007377-204

x: t_<!

" RAE2129AIRCRAFTINTAKEDUCT .'_

,CompressorFaceTotal Pressure6 6 '_ Offset/Length= 0.50, M- 0.608,Re- . 1x 10

.i

i _'L_---_-.-,_ 11117

'.r

Analysis( No Hub) Experiment '_

tRAE2129AIRCRAFTINTAKE.DUCT i

,CompressorFaceTotal PressureOffset/Length= 0.50, M- 0.412,Re- 4.1,.5x 106 _

-i -

,Analysis( No Hub) Experiment I_

1989007377-205

2,]I _i,_,_

RAE2129AIRCRAFTINTAKEDUCT.CompressorFoceTotol Pressure

Offset/Length= 0.,t0, M= 0.794,Re= 6.60x 106

i '

.2 AnGlysis(No Hub) ExperimentJ

\RAE2129AIRCRAFTINTAKEDUCT

.CompressorFoceTotal PressuOffset/Length= 0.45, M= 0.,.t85,Re- 5e90x 106

Anolysis( No Hub) Experiment :_

1989007377-206

RAE2129AIRCRAFTINTAKEDUCTCompressorFaceTotal Pressure

_' Offset/Length= 0.45, M= 0.77,3,Re- 6.50x 106It

t

r

J

i

!4

Analysis( No Hub) Experimenti

\

RAE2129AIRCRAFTINTAKEDUCT• ,CompressorFaceToto Pressure

Offset/Length= 0.45, M= 0.57,_t,Re- 5.,37x 106

!

Analysis( No Hub) Experiment

1989007377-207

1989007377-208

1989007377-209

i

1989007377-210

1989007377-211

' ORIGINALPAG

,, OF POORQUALITY 't4't

UNIVERSITYOFTENNESSEEINLETDUCT iCirclJlar50-50 degree Inplane ,._-Bend

Total Pressure Contours, No Vortex Generators•. X/D- .29

1

Analysis Experimen[

i\

UNIVERSITYOF-TENN.%{_-.....oE.EINII-r i)u_:iCircular 50-50 degree Inp,r;rleS.....E!cr_d i

-I-oralPressure Contours, No Vorte.x C.er!crut(,rs tX/'D- 2.4.9

I-I

Analysis t::,:p_,:ironenI

1989007377-213

ORIGINALPAGE IS _,

' OF POOR QUALITY: UNIVERSITYOFTENNESSEEINI_.I:.II[DII]CI "q/

, Circular 50-,]0 degree Inplan_._S-B,?t;d' Total Pressure Contours, No Vc:,rtr;xOertorator:s

X/D=s.7o

Analysis Experiment

IJNIVERSITYOF]ENNE""......'.... r:i:),:)E.LI.. r'i[i.... [')j r

C;rcular 50-50 degree npl,a_,.::,':i---[.i,:r_,i iTara! Pres{" e.oLir Contc)urs,No:)Vort,,x Cr_,rl,,r_:!_.,r{"

', . . ' L.... ) t

X/D - _-)r',_,

1

t

Analysis '

1989007377-214

1989007377-215

1989007377-216

?

_ -D

,- ORIGINALPAGE IS_,_ ._._o OF POOR QUALITY

- _ _

vo Q..)

_0

°_ LLICD I0_" I I I'

_"_ X 0

•,_E _,

,,, _.

o

la

•1_ iIJ_. U'3 _3t.,t_/

• _' f'Y" 0"_ IJ_l _J_ ,,4 _

• • _7,10 _.H

O=la

0'_

"* _ 0• ,_4_j¢ ,_

1

®

l .....................................................................1989007377-217

1989007377-218

_, ORIGINALPA_E 13' OF POOR QUALITY ,

" UNIVERSITYOFTENNESSEEINL.ETDUCT, Circular,30--50degreeInplaneS--Bend ii_, Total PressureContours,VortexCeneratorr:_

X/r") .,, _.: -!29

I

!

i," Analysis Experiment

It:9

\

UNIVERSITYOFTENNESSEEINI....E....DUC.[Circular,30-50 degreetripan,!-'.S--Ei,:_r-_d

Taro Pressun-_,.Contours,Vortex(..terlera!:orsX//D- 2.49

2

L

;' jt

A a y_l,:, Exp_:rlment_. nl _,'_.... •

1989007377-219

ORZGfr_ALp_ ISOF POOR QUALITY' i_ ,-'!

UNIVERSITYOFTENNESSEEINLETDU(:TCircular50-30 degreeInplaneS....Bend

Total PressureContours,VortexOenera!orsI1 r) ] "7, X/L 370

Ariaysis [!xperimfmt

1989007377-220

1989007377-221

b K,

i

: ORIGINALPAGE ISOF PC.ORQUALITY

J

I....1989007377-:

1989007377-223

,!

_, F20COMPUTATIONALSTUDYINLETGeometryDefinition,DownstreomView

i In-PloneOffset,Offset/Lenqth- 0.2_ Aexit/Ainlet= 1.42_

F

I

\

F30COMPUTATIONALSTUDYINLETGeometryDefinition,DownstreomView

' StroiahtCenterlineInletDuct,, Aexit/Ainlet= 1.42L-

1989007377-224

.....19890-07377-225

1989007377-226

II! /,

, 1

CFDVALIDATIONEXPERIMENTModels A CircularArc (R/r = 5.6) RoundDiffuserof Are(] Ratio

1.5 will be Arrangedin the Formof two Connecting90.0 DegreeBen[Isso as to Allowo 180 deqreeInplone,90-90 out-of-plane, and 90-90 InploneDiffusingDuct

Conditions For EachDuct,ThreeSets of SeparatedFlowData willbe Obtained;for LaminarFlowat NominalReynoldsNumberof 500 and 1093, and TurbulentFlowat oReynoldsNumberof 43,000

Analysis A Pre-Test Anoly.siswill be Performedto Establishthe_FlowSeparationTopologiesand howthey are EffectedbyReynoldsNumber,BoundaryLayerThickness,and Swirl

Meosurments Experimentswill be Carriedout with CombinationsofLaser-Velocimetry,Hot WireAnenometr!/,PressureTubes,endRow Visualization.SurveyPlaneswillbeEstablishedfromAnalysisoftheComputationalResults

I!

CFDVALIDATIONEXPERIMENT tTitle ConfinedSeparationin CurvedDiffusingDucts '

Ii

Objective Establisha DetailedExperimentalDot(]Bosefor #Evaluationof NovierStokesCodesfor ConfinedSeparatedFlowsin CurvedDiffusingDucts

Thrusts Extensionand Vclidotionof LewisPNSSolverintoSeparatedFlowRegimeusing FlareApproximationsEvaluationand Extensionof State-of-the-Art -,

Tu-Modelsfor Confined,Separated,SwirlingFlows jEvaluationand Validationof LewisTimeMarching tNS Solver(PROTEUS)into SeparatedFlowRegime

Approach A Joint Analysis/ExperimentalProqromwill be - iInitiatedin whichthe ExperimentalMeasurmentswillbe Performedat a University,and the Analysis

I at LewisResearchCenter "

b ®ti ! i

1989007377-227

4 I

CONFINEDSEPARATIONINCURVEDDIFFUSINGDUCTS ,,, CFDValidotionCoses

ReynoldsNo. Swirl iFlow 6/R Conf.1 Conf.2 Conf.3Angle

500.0 Laminar 0.2 0.0 CS CS CS30.0 CS CS CS

I 45.0 CS CS CS

1.0 0.0 CS CS SF45.0 CS CS CS

1093.0 Lominor 0.2 0.0 CS CS SF30.0 CS CS SF

t 45.0 CS CS CSi" 1.0 0.0 CS SF SF"' 45.0 CS SF SF

f 43,000 Turbulent 0.2 0.0 CS CS SF

15.0 CS CS CS30.0 CS CS CS

1.0 0.0 CS SF** SF**30.0 CS CS CSL.i AF- AttochedFlow CS- ConfinedSeporotion SF- SeporotedFlowIt

# #

I CFDVALIDATIONDIFFUSINGDUCTS \180 DegreeInploneGeometry

ConfigurotionNo. 1

t

N

1989007377-228

CFDVALIDATIONDIFFUSINGDUCTS _,_ 90/90 Out-of-Plone Geometry _

ConfigurotionNo. 2

N

CFDVALIDATIONDIFFUSINGDUCTS \90/'90DeqreeInploneGeometry

ConfigurotionNo. 5 i

1989007377-229

1989007377-231

®

1989007377-233

1989007377-234

1989007377-235

1989007377-236

®

1989007377-237