C.X • DOC NUN SER CN MAY & 1988 JPlUIilRORilIlllUI I I › dtic › tr › fulltext › u2 ›...
59
AEDC-TSR-79-V 71 C.X • ~33~ ~33=b UNCLASSiFtE~ DOC NUN SER CN UNC28864-PDC A 1 JPlUIilRORilIlllUI I I U| UUIiPlIi IlilIIII|IllilIIlIIRII ! . BOUNDARY LAYER MF.ASUREMEI~ITS Oil SLENDER BLUNT COrlES AT - FREE-STREAM MACH NUMBER 8 . ~-x , ~,;" G. Stler and 3. C. Donaldson AR0, Inc. JO- .' :' 5~0 MAY & 1988 DEC 2 2~ 1990 APR 2 4 1997. December 1979 Flnal Report for Perlod 21 Sept:ember 1979 - 25 Sepl:ember 1979 f. ,,'~, .,i,- r, , r-: ;v"'-, ,, C-d;,J:] . j Approved ~o,- pubU¢ ,,elea-~e; dis;.r:LbutionunZ~i-t:a.- . . . . . . ................................ TECHlq :CAL R EPOI" S .F~LE ~COPY.. e ~- .° -o Property of U. S. Air Foeoll A£DC LIBRARY F49G@O- 17-C.060,1 PROPERTY OF U.S. AIR FORCE AEDC TECHNICAL LIBRARY ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AIR FORCE STATION, TENNESSEE • AIR FORCE SYSTEMS COMMAND UNITED STATES AIR FORCE UNCLASSmmD
Transcript of C.X • DOC NUN SER CN MAY & 1988 JPlUIilRORilIlllUI I I › dtic › tr › fulltext › u2 ›...
AEDC-TSR-79-V 71 C . X •
~33~ ~33=b
UNCLASSiFtE~
DOC NUN SER CN UNC28864-PDC A 1
JPlUIilRORilIlllUI I I U| UUIiPlIi IlilIIII|IllilIIlIIRII ! .
BOUNDARY LAYER MF.ASUREMEI~ITS Oil SLENDER BLUNT COrlES AT
- FREE-STREAM MACH NUMBER 8 . ~-x ,
~,;" G. Stler and 3 . C. Donaldson
AR0, Inc.
JO- .' :' 5 ~ 0
MAY & 1988
DEC 2 2 ~ 1990
APR 2 4 1997.
December 1979
F l n a l Report f o r P e r l o d 21 Sept:ember 1979 - 25 Sepl:ember 1979
f . , , '~,
. , i , - r , ,
r-: ;v" '- , , , C-d; ,J : ]
. j
Approved ~o,- pubU¢ ,,elea-~e; dis;.r:Lbution unZ~i-t:a.- . . . . . .
................................
TECHlq :CAL R EPOI" S .F~LE ~COPY..
e
~ - . ° - o
Property of U. S. Air Foeoll A£DC LIBRARY
F49G@O- 17-C.060,1
PROPERTY OF U.S. AIR FORCE AEDC TECHNICAL LIBRARY
ARNOLD ENGINEERING DEVELOPMENT CENTER
ARNOLD AIR FORCE STATION, TENNESSEE
• AIR FORCE SYSTEMS COMMAND
UNITED STATES AIR FORCE
UNCLASSmmD
u w s~
L . I - ~
. " . . . ~ . ~ ° . . . .
- . . . .
. . ' . ,& ~ , ' - . ' - ~ " " . I . . " ~ • ." - " " .
, q - .
o .
J
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v ' . -
• " . N o : r I C E S
When U. S. Government drawings, specifications, or other data are used for any purpose other than a definitely related Government procurement operation, the Govemmnent thereby incurs no responsibility nor any obligation whatsoever, and the fact that the Government may have formulated, turn/shed, or in any way supplied the said drawings, specificat/ons, or other data, is not to be regarded by implication or otherwise, or in any manner licensing the holder or any" other person or corporation, or conveying any rights or permission to'manutacture, use, or sell my patented invention that may in any way be related thereto.
References to named comrnerical products in this report are not to be considered in any sense as an indorsement of the product by the United States Air Force or the Government.
• - %
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Q
, - . , .
, - A P P R O V A L S T A T E M E N T
Th/s report has been reviewed and approved.
JOSEPH F. PAWLICK~ Jr., Lt. Col, USAF Test Director, VKF Division Directorate of Test Operations
Approved for publication:
FOR THE COMMANDER
- - . o
JOHN C. HARTNEY, Colonel, USAF Director of Test Operations Deputy for Operations
II~ 8= I
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4 "
REPORT DOCUMENTATIOH PAGE - | . REPORT NUMBER . . • . . 12. GOVT ACCESSION NO,
AEUC-TSR-79-V71 . . . . " ]~" • " 4. T I T L E ( ~ d ~ubf l l le ) Boundary Laye r Measurements on S lende r B l u n t Cones a t F r e e - S t r e a m H a c h Number 8
7. AUTHOR(s)
L. C. Siler, and J. C. Donaldson, ARO, a Sverdrup Corporation Company
U H C L A S S I F I E D - "
• i R E A D I N S T R U C T I O N S [ B E F O R E C O M P L E T I N G F O R M
9 PERFORMING ORGANIZATION NAME AND ADDRESS
Arnold Engineering Development Center/DO Air Force Systems Command Arnold Air Force Station, Tennessee 37389
I n c . ,
, , . CONTROLL,NG OFFICE MAME AND ADDRESS
A i r Force F l i g h t D ~ a m i c s Labo ra to r y /FXG W r i g h t - P a t t e r s o n A i r Force Base, Ohio 45433
14. MONITORING AGENCY NAME & ADDRESS( I / d l l l o ren t Irom Ccmt ro l l i n80 [ l i co )
3, R E C i P I E N T ' S C A T A L O G NUMBER
S. TYPE OF REPORT & PERIOD COVERED
F i n a l Repor t - September 21 to ~5, 1979 @. PERFORMING ORG. REPORT NUMBER
li. CONTRACT OR GRANT NUMBER(s)
10. PROGRAM ELEMENT. PROJECT. TASK AREA a .oRK UN,T NUMBERS
Program Element 61102F
, z . REPORT DATE "December 1979
|S. NUMBER OF PAGES
56 1S. SECURITY CLASS• (o l this ~;p~rt)
U n c l a s s i f i e d
ISe. DECL ASSI F ICATION/DOWN GRADING SCNEDULE N/A
IS. D ISTRIBUTION STATEMENT ~ol fhJc Be3Po|'|)
:Approved f o r p u b l i c r e l e a s e ; d i s t r i b u t i o n u n l i m i t e d .
• !
i
|? . D ISTRIBUTION STATEMENT (o l ~ o obltvRct t u to red In B lock 20, i l ~ I IeeM# ~om ReporO
1|• S U P P L E M E N T A R Y NOTES
A v a i l a b l e i n De f e nse T e c h n i c a l I n f o r m a t i o n C e n t e r (DTIC).
19. KEY WORDS ( C a n t i n g ~ reverse aide Jl nocoseary -md t den t l~ by block numbe~
h y p e r s o n i c f low b o t - v l r e anemometer b l u n t b o d i e s ~ o u n d a r y l a y e r s t a b i l i t y wind t u n n e l t e s t s l a m l n a r bounda ry l a y e r s u r v e y s a d l a b a t l c - w a l l tests
20, ABSTRACT ( C o n | l n ~ m a v e r s e smdo I f necessary m d f d e n t t ~ by block f lumbo~
Boundary l a y e r p r o f i l e s and s u r f a c e c o n d i t i o n s were measured on a s l e n d e r cone w i t h v a r i o u s nose b l u u t n e s s e s w i t h a l a m i n a r bounda ry l a y e r and w i t h t h e w a l l t e m p e r a t u r e i n a s t a t e o f e q u i l i b r i u m . The measurement s were made a t a f r e e - s t r e a m Mach number o f 8 f o r u n i t Reynolds numbers f rom 1.3 t o 3.5 m i l l i o n p e r f o o t . Su rveys were made u s l n g a h o t - w i r e anemometer and t o t a l t e m p e r a t u r e and p r e s s u r e p r o b e s . D e s c r i p t i o n s o f t h e t e s t a p p a r a t u s , p r o c e d u r e s , and t e c h n i q u e s used a r e g i v e n i n t h l s r e p o r t .
5
FORM 1473 EDIT,ON OF ' . O V 6 S , S O " S O L E T t D D , j A N .
- ' l l W r l / ' , ~ . ~ l r n •
. ° %
. , ¢ ~ - - . . . c
" : 2 , ~ ' - - - - - ' - - - ~ " ~ - - " : - - - , - " - = : ' ~ : : = T ' " - = - - - - ~ - - - - - - ~ . . . . . . . . : - - ' " ~ - : Y - : : : ' = " : - - - - "1 ~ " - .
J I - . _ .'
" ' . ; ~ . . . ~ .
NOMENCLATURE . . . . 3
1 0 I N T R O D U C T I O N • • . 9 • • • • • • • • . • • • • •, • ' " m • • • • • • • • • • •
, ~ . . . . - : - . - - 2 7 0 .. . . APPARATUS- . . ~ , ~ /.;
- 9 - 2 1 Test Facfllty: , - - • • • 0 - • • • " • • • • • • • - • • • • • • • • • •
- - 2 2- T e s t Article I0
2.3 Flow Field Survey Mechanism . . . . . . . . . . . . . . . I0
• "'- "2.-4--l~low-Yleld-P~ob es ........... , II • • • • • • • • • • • • • • • • • • • Ip
--.--- " " - 2;5 Test Instrumentation
:- - ..... 2 5 1 Tunnel Conditions II = . • - o • • • • g • • • IJ • • • • • • •
:---= ...... 2.5.2 Model Surface H e a t Transfer Measurements ..... 12
. .......... : --~-~,5.-3. Hot Wir~ Anemometry . , . . . . . . . . , .... 12
3.0 TEST DESCRIPTION .... .
' : ' : - -'- : : . ~ ' : " - " - - 3 ; i - " T 4 ~ £ " C b n d l h l b h s a n d P r o c e d u r e s • ,,[_--i- "-----'---" ~ ""
3 1 1- General 13 " • • • • • • • • • • • • • • • • • • • • • • • •
• . - . - /7: - ~ = I : - 2 - : - D a t a - A c q u i s i t i o n 1 3
3.1.3 Hot-Wire Anemometer Probe Calibration . . . . . . 16
3.2 Data Reduction . . . . . . . . . . . . . . . . . . . . . 17
3 3 Uncertainty ~f Measurements 18
4 . 0 DATA PACKAGE P R E S E N T A T I O N . . . . . . . . . . . . . . . . . . . 1 9
~--~ 5 G EEFERENCE$ ...... 20 4
I. ILLUSTRATIONS - .
"~-~ "z=~=~E • " D- ~-.:.~.£'-.- .~:..~--~=a~.-~..-~.=.~ ~.=~-
1 . T u n n e l B . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 2
2. Model Geometry and Gage Locations . . . . . . . . . . . . . . 23
3. Test Installatibn . . . . . . . . . . . . . . . . . . . . . . . . 24
Probe-Details 25 • e D o o o e Q e o a e e o e o e e e o o o e e o
5. Sketch of Survey Probe Rake . . . . . . . . . . . . . . . . . 26
6 Closed-Circult Television System 2 7 • o e m o o o u o o e e m • o •
.,=;~_L~=7, Typical TotalTemperature Probe Calibration . . . . . . . . . 28
8. Model Surface Pressure Distributions . . . . . . . . . . . . . 29
• 9~ .... ~ustrat~o~-of: He~t-TransferDistrlbutlon Results . . . 30
I0. Illustration of Qualltatlv@ Hot-Wire Anenometer
Profile Results ...... . . . . . . . . . . . . . . . . . . 31
-'~ 11. Illustration of Mean Flow Boundary Layer Survey Results . . . 32
.1." L'i .... L- . . . . . . :."
, ~i..~.=ll. -" . . . . U = " "
• ° , +
• " • • ,o
. . . . . . . . . . . . . • ' . . . . . ' . . . . , :- + . ; . . ~ ; ~ ; " '
. . . . . . . . . . . . . . . - - . - . " . . , . . . . . .
I I . TABLES I . . . . . -+ • ' " " 41, ' • ' .
T a b l e . . . .
e-_mm.
• ------ 37 1 M o d e l I n s t r u m e n t a t i o n L o c a t i o n s • • • • • • . • • • • • • • • • • • • •
2 Estimated Uncertainties -' - . . . . 39 • • • • • • • • g • • • • • • • • • • • •
3 . T e s t Summary . . . . . . . . . . . . . . . . . . . . . . . . . 4 2
"" 4 Survey Stations 4 6
III. SAMPLE DATA
1• D a t a Type: S u r f a c e H e a t T r a n s f e r . . . , . . . . . . . . . . e 4 8
2• D a t a Type 2 , Model S u r f a c e M e a s u r e m e n t s . . . . . . . . . . . . 4 9
3 • D a t a Type 13, F low F i e l d S u r v e y . . . . . . . . . . . . . . . . 5 0
4~ D a t a Type 4 , F low F i e l d S u r v e y . . . . . . . . . . . . . . . . 5 1
5• D a t a Type 6i F r e e - S t r e a m P r o b e C a l i b r a t i o n . . . . . . . . . . 5 5 :
6• D a t a Type 9 , Hot Wire Anemomenter D a t a . . . . . . . . . . . . 5 6 +
• °
- - I , r " . . . . . i P i p •
i
,%
, , . . . . ; . .
l l .
• _ o . . - ~ . . ' . . . I I I I i ~ . . .
. . ' . ~
Q
NOMENCLATURE
" . . . . : - . " . -- b. -
ALPIlA, ALPHA-SECTOR, a
CONFIGURATION
'C.R.
.'.. o"
Angle of a t t a c k , deg
Model c o n f i g u r a t i o n d e s i g n a t i o n
Center of rotation~ tunnel centerline axial station about which model rotates in pitch, in.
CURRENT
DATA TYPE
DEL, 6
DEL*
DEL**
Hot-wlre heating current, ma
Thermocouple j u n c t i o n d i a m t e r , 0 .005 i n . .
Code indicatin8 nature of data tabulated~
HEAT TRANSFER - Cold wall model surface heat- transfer measurements
112'1
I1~11
"4"
11~1f
Model surface pressure measurements
Qualitative hot-w~re anemometer and total temperature probe boundary-layer profile measurements -. "--
Mean boundary layer profile measurements using pitot pressure, and total temperature probes
Total temperature probe calibrations
11911 Quantitative hot-wire anemometer data a t particular point locations within a survey
Boundary - layer t o t a l t h i c k n e s s (where UL/UE = - 0 . 9 9 5 ) , in . -.-~ . . . % °
Boundary- layer d i sp lacemewt t h i c k n e s s , i n .
Boundary- layer momentum t h i c k n e s s , in .
DEW PT F r o s t p o i n t , °F
3 ~- "% . .~ ... ..'.--
-. . '. . . o ~ • ,
. . . . . . . .- . -.." .'-''" '_.. .~-" • " : ' - . C ~ ' - , ~ . " " " - -
DITTD
DITTL - . ~ . . ~ . . . : . _
:'EBAR
L o c a l e n t h a l p y d i f f e r e n c e ,
. ~ . . - ~ - . : ~ - ~ = ~ . . . . . . . . . . . . . . . . . . . .
. . . . . Hot-wire mean voltage, my
: E n t h a l p y d i f f e r e n c e a t b o u n d a r y - l a y e r t h i c k n e s s , DEL, TTTD-ITWL, B t u / l b m
ITTL-'rTW, B e u / l b m
ERMS .. ° Anemometer output rms voltage, mv
ETA
_ H(TT)
ITT "
ITTD
.."
Effective total-temperature probe recovery factor
j : . _ . = ~ - - ~ " . . _ - ~• - . _ _
_ Heat transfer coefficient based on TT, QDOT/(TT_TW),Btu/ft2_sec_OR
. - ° - . . . . . . ~ . . . . .
" - E n t h a l p y b a s e d on s t i l l i n g chamber t o t a l ~ temperature, ~ gtu/Ibm ". .....
J
E n t h a l p y b a s e d on TTD, B t u / I b m
. . . . .
ITW . o :
. . . , ,~^.: . . ..... ITWL
" " ' - ' - 'Enehalpy b a s e d on TTL, B t u / i b m -
i
- E n t h a l p y b a s e d on m o d e l w a l l t e m p e r a t u r e , B t u / l b m
' . | . '
" - - ' " '" ~ - i ~ n t h a I p y bas'ed on ~ I , , B t u / l b m . . . . . . . . . . .
LRE . -~ • . . ° .
LRED '
LRET
m p
Local unit Reynolds number, in. ~I
Unit Reynolds number at the boundary-layer thickness, DEL, in. "I
Local "normal shock" unit Reynolds number ( b a s e d on MUTTL), i n . "1
LRETA .... !'Normal shock" unlt Reynolds number at ZA (based on MUTTL), in:-1
LRETD
. l o
"Normal shock" unit Reynolds number at boundary-la~er thickness, DEL (based on ~V~TD), in. -~
II d ~ w m~
.- , , - . - . . - ~. . . ~ ' . .
o . .- .
• - , . : . . . . .
M, MACH
MA
r • q
m
, , • • • " .
, ,.~--
• . , . .
I ' '
Free-stream Mach number
L o c a l Ma~h number a t ZA
' L o c a l Mach number a t b o u n d a r y - l a y e r ' t h i c k n e s s , DEL, i n . - 1
I ,
. °
ME Mach number a t b o u n d a r y - l a y e r edge
ML L o c a l Mach number
MODEL ROLL, ROLL
MU
MU'I'D MUTL
MUTT MUTTD
MUTTL
P
° Q . ,.
PHI,
PITCH %
PP
PPD
PPE
Roll angle, deg
Dynamic viscosity b a s e d on T, I b f - s e c / f t 2
Dynamic v i s c o s i t y b a s e d on TD, l b f - s e c / f t 2
Dynamic v i s c o s i t y ba sed on TL, l b f - s e c / f t 2
Dynamic viscosity based on TT, Ibf-sec/ft 2 Dynamic viscosity base~ on TTD, Ibf-sec/ft 2
Dynamic viscosity based on TTL, ibf-sec/ft 2
Free-stream static pressure, psia
R o l l a n g l e , deg
Ang le o f a t t a c k , deg
P r o b e pltot p r e s s u r e , p s i a
P i t o t pressure a t boundary-layer thickness, DEL, psia
Pitot pressure at boundary-layer edge, psia
PT
PT2
Tunnel stilling chamber pressure, psla
Free-stream total pressure downstream of a normal shock wave, psla
m ~ ~mm
-. , . .~ . . .
~ m I# B ~
• , - - .
PW
PWL
Q
QDOT
RE,RE/IN.
RE/t
PET . .
RHO
~ O D
~ O L
- , , ° |
aN, RADIUS
B
Model s u r f a c e p r e s s u r e , p s i a
Model wall static pressure used for boundary-layer survey, psia
Free-stream dynamic pressure, psia
Heat transfer rate, Btu/ft2-sec
Free-stream unit Reynolds number, in. -I
Free-stream unit Reynolds number, ft -I
Free-stream "normal sh~ck" unit Reynolds number (based on MUTT), in. -1
Free-stream density, Ibm/ft 3
Densit~ at boundary-layer thickness, DEL, lbm/ft ~
Local density, lbm/ft 3
(RHOD) • (UD), ibm/secrEt 2
Model n o s e r a d i u s , i n ,
Data set identificatlon number •
,f m
SD PW
Curvillnear surface distance from model stagnation point, in.
Model wall pressure standard deviation
SD TW Mode l wall temperature standard deviation
SREF
ST(TT) , STTNF
Model reference curvillnear surface distance (from stagnation point to base), in.
Stanton number based on stilling chamber QDOT
temperature (TT), ST(TT) = (RHO) (V) (ITT-ITW)
• o:. ,,. :" 6
i • . . • . . • . i/ ,
v • " " . . . . , ' . , , • • " .
T .. Free-stream static temperature, "R - . . o
/TAP
T/C
r I %
P r e s s u r e o r i f i c e i d e n t i f i c a t i o n number
Thermocouple i d e n t i f i c a t i o n number
. , . ~ :
. TD ; ~, $ t a t l c t emperature a t b o u n d a r y - l a y e r " - ' .
t h i c k n e s s , DEL, °R
TDRK
, .
. Temperature o f druck t r a n s d u c e r , "F
~[ETA, 0
TL
TRIP
P e r i p h e r a l a n g l e on the model measured from ray on model top , p o s i t i v e c l o c k w i s e when . l o o k i n g upstream, deg
Loca l s t a t i c t emperature , °R
Boundary-Layer t r i p ~ d e n t i f i c a t i o n
Tf
TTA
TI~ ...j
Tunnel s t i l l i n g chamber t emperature , °R
Total temperature at ZA, "R
T o t a l t emperature a t b o u n d a r y - l a y e r t h i c k n e s s , DEL, OR
TEE
TEL
Total temperature at boundary-layer edge, °R
Local total temperature, ~R
TTLU Dncorrec ted (measured) probe t o t a l t e m p e r a t u r e , i n t e r p o l a t e d a t ZP, °R
TTTU o
TW
L~correc ted (measured) probe t o t a l t empera ture , °R
Model surface temperature,'°R
TWL Model wall temperature used for boundary-layer s u r v e y , °R
• • o
. - , . , . ,
, . , ~ 4 ' , - - -
L' , . • " , .
I
" c. ...... p
UD Local velocity component parallel to model surface at boundary-layer thickness, DEL, ft/sec
UE Local velocity component parallel to model surface at boundary-layer edge, ft/sec
UL
V
Local v e l o c i t y component p a r a l l e l to model s u r f a c e , f t / s e c
F r e e - s t r e a m v e l o c i t y , ft/sec
X Axial location located from virtual apex of 7-deg cone model, in.
ZA
ZP
ZT
~ . . = °
Anemometer-probe height, distance to probe sensor along normal to model surface, in.
Pitot-pressure probe height, distance to probe centerllne along normal to model surface, in.
Total-temperature probe height, distance to probe centerline along normal to model surface, in.
7 "
, . , , • . • . , , . . • , . . . . , . . . , : • . . . . .
"", 8 . . °- ".-
1 . 0 INTRODUCTION
The work r e p o r t e d h e r e i n was c o n d u c t e d by t h e A r n o l d E n g i n e e r i n g Deve lopmen t C e n t e r (AEDC), A i r F o r c e Sys tems Command (AFSC), u n d e r Program Elemen t 61102F, C o n t r o l Number 2 3 0 0 - 9 9 - 9 , a t t h e r e q u e s t o f t h e ~ / r F o r c e O f f i c e o f S c i e n t i f i c R e s e a r c h ( A F O S R / N A ) , B o l l i n g A i r F o r c e Base , W a s h i n g t o n , D.C. f o r t h e A i r F o r t e F l i g h t Dynamics L a b o r a t o r y ~VFDL/FXG), W r i g h t - P a t t e r s o n A i r F o r c e Base , AFSC, W r i g h t - P a t t e r s o n A i r F o r c e Base , Oh io . The AFOSR/NA p r o j e c t m o n i t o r was Dr. James W i l s o n and t h e AFFDL/FXG p r o j e c t m o n i t o r was Mr. Kenne th S t e t s o n . The r e s u l t s were o b t a i n e d by ARO, I n c . , AEDC . D i v i s i o n .(a S v e r d r u p C o r p o r a t i o n Company), o p e r a t i n g c o n t r a c t o r f o r t h e AEDC, AFSC, A r n o l d A i r F o r c e S t a t i o n , T e n n e s s e e . The t e s t was c o n d u c t e d i n t h e yon Karman Gas Dynamics F a c i l i t y (VKF), T u n n e l B d u r i n g t h e p e r i o d S e p t e m b e r 21 t h r o u g h 25, 1979, u n d e r ARO P r o j e c t No. V41B-B2.
The t e s t o b j e c t i v e was t o e x p e r i m e n t a l l y i d e n t i f y t h e t u r b u l e n c e mechan i sm w i t h i n a l a m i n a r b o u n d a r y l a y e r w h i c h p r o m o t e s b o u n d a r y - l a y e r t r a n s i t i o n on a b l u n t body o f r e v o l u t i o n i n a h y p e r s o n i c s t r e a m . To a c c o m p l i s h t h i s , f l o w f i e l d s u r v e y s we re o b t a i n e d a t a f r e e - s t r e a m Mach number o f 8 u s i n g a p r o b i n g s y s t e m i n s t r u m e n t e d w i t h a h o t - w i r e a n e m o m e t e r , a t o t a l t e m p e r a t u r e p r o b e , and a p i t o t p r e s s u r e p r o b e . The mode l c o n - f i g u r a t i o n u s e d was a 7 - d e e ( h a l f - a n g l e ) cone w i t h f o u r i n t e r c h a n g e a b l e n o s e t i p s o f v a r i o u s b l u n t n e s s ( s h a r p , 3%, 10%, and 40% r e f e r e n c e d t o t h e b a s e r a d i u s ) . T e s t s were c o n d u c t e d a t a s i n g l e f r e e - s t r e a m u n i t R e y n o l d s number f o r each b l u n t n e s s c o n f i g u r a t i o n r a n g i n g f rom 1 . 0 to 3 .5 x 106 p e r f o o t . A l l s u r v e y s w e r e made a t z e r o - ' a n g l e o f a t t a c k a t e q u i l i b r i u m
• w a l l t e m p e r a t u r e s (TW/TT o f a p p r o x i m a t e l y 0 . 7 5 ) . Model s u r f a c e p r e s s u r e , " i h e a t - t r a n s f e r , and t e m p e r a t u r e d i s t r i b u t i o n s were a l s o o b t a i n e d .
. . . . . . . . . . . . . = .......................................
I n q u i r i e s t o o b t a i n c o p i e s o f t h e t e s t d a t a s h o u l d be d i r e c t e d t o _APFDL/FXG, W r i g h t - P a t t e r s o n A i r F o r c e Base , Ohio 45433. A m i c r o f i l m record h a s been r e t a i n e d i n t h e VKF a t AEDC.
2.0 APPARATUS ~ h
2oi TEST FACILITY
T u n n e l B ( F i g . 1) i s a c l o s e d c i r c u i t h y p e r s o n i c wind t u n n e l w i t h a ~50-1n.-diam test section. Two axisymmetric contoured nozzles are available to provide Math numbers of 6 and 8 and the tunnel may be operated contin- uously over a range of pressure levels from 20 to 300 psla at Math number 6, and 50 to 900 psia at Math number 8, with air supplied by the VKF main compressor plant. Stagnation temperatures sufficient to avoid air • liquefaction in the test section (up to 1350"R) are obtained through the use of a natural gas fired combustion heater. The entire tunnel (throat, nozzle, test section, and diffuser) is cooled by integral, external
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water Jackets. The tunnel is equipped with a model injection system, which allows removal of the model from the test section while the tunnel remains in operation. A description of the tunnel may be found in the Test Facilities Handbook, Ref. I~
iI 2.2 TEST ARTICLE
The basic model configuration was a 7-deg half-angle cone with a virtual length of 40 in. as shown in Fig. 2. Model nose bluntnesses of 0.150-in. (3% bluntness), 0.500-in. (10% bluntness), and 2.000-in. (40Z bluntness) radius were tested in addition to the baseline sharp nose (RN = 0.0015 in.) configuration. Model components were fabricated from type 304 stainless steel at the AEDC.
. . . . . . . . . . . . . . | . . . . . . . . .
The model was instrumented with pressure orifices and coaxial surface thermocouple gages. Table 1 (Appendix II) lists the instrumentation 1ocatlons and indLcates that the top centerllne (8 = O) was the main ray of pressure instrumentation and the bottom centerllne (8 = 180 deg) was the only ray instrumented with thermocouple gages. Pressure orifices were also installed on the 8 = 180 and 270 deg rays at three additional axial stations.
A model installatlon photograph is presented in Fig. 3.
2°3 FLOW FIELD SURVEY MECHANISM
Surveys of- fiei using system (X-Z Survey Mechanism) designed and fabricated by the VKF. This mechanism makes 'it possible to change survey probes while the tunnel remains in operation. The mechanism is housed in an air lock J~emediately above a port in the top of the Tunnel B test section. Access to the test section is through a 40-in.-long by 4-in.-wide opening which'can be sealed by a pneumatically-operated door when the mechanism is retracted. Separate drive motors are provided to (i) insert the mechanism into the test section or retract it into the
: housing, (2) position the mechanism at any desired axial station over a range of 35 in. and (3) survey a flow field of approximately 10-in. depth. The survey mechanisms were used in combination to traverse
i the probes across the flow field. A pneumatlcally-operated shleld was i provided to protect the probes during injection and retraction through .the tunnel boundary layer, during changes in tunnel conditions, and at times when the probes were not in use.
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2.4 FLOW FIELD PROBES : ", • •
The pltot-pressure probe was made by flattening a 0.025-in. O.D. (0.020 I.D.) tube, as shown in Fig. 4a, which produced a probe tip thickness of 0.011 In. with an open sllt height of 0.006 in. The tube section behind the orifice tube was bent in such a manner as to hold the probe alignment parallel to the model surface during the surveying sequence. . :
The hot-wlre anemometer" probes were fabricated by the VKF. Platlnum-10Z rhodium wires, drawn by the Wollaston process, of 20-~ in. nominal diameter and approximately 150 diameters length, were attached to sharpened 3-mll nickel wire supports using a bonding technique developed by Philco-Ford Corporation (Ref. 2). The wire supports were inserted in an alt~mlna cyllnder of 0.031-1n. dlam and 0.25-in. length, which was, in turn, cemented to an alumina cylinder of 0.094-in. dlam and 3.0-1n. length that carried the hot-wlre leads through the probe holder of the survey mechanism.
The unshlelded total temperature probe was fabricated by the VKF from a length of sheathed thermocouple wire (0.010-1n. O.D.) with two 0.O015-1n. diameter wires. The wires were bared for a length of about
• 0.015 in. and a thermocouple Junction of approximately 0.007-in. diam~s ,~ade. Details of this probe are shown in FiE. 4b.
A s k e t c h o f t h e s u r v e y p robe r a k e u s e d d u r i n g t h e test i s i l l u s t r a t e d i n F i g . 5 .
ZSS em STATIOS . , _ . . . . . . . . . . . . . . . : •
2,5.1 Tunnel Conditions
The m e a s u r i n g d e v i c e s , r e c o r d i n g d e v i c e s , and c a l i b r a t i o n m e t h o d s ~ f o r a l l m e a s u r e d p a r a m e t e r s d u r i n g t h i s t e s t , w i t h t h e e x c e p t i o n o f t h e 7 h o t - w l r e anemomete r i n s t r u m e n t a t i o n , a r e l i s t e d i n Tab l e 2 a l o n g w i t h
t h e e s t i m a t e d m e a s u r e m e n t u n c e r t a i n t i e s . The u n c e r t a i n t i e s i n t h e . s t i l l l n g chamber p r o p e r t i e s , a s i t e m i z e d i n t h i s t a b l e , a r e u s e d i n c o n j u n c t i o n w i t h p r e v i o u s l y e s t a b l i s h e d n o z z l e Mach number c a l i b r a t i o n s
• as t h e b a s i s f o r d e f i n i n g t he u n c e r t a i n t i e s i n t h e t e s t s e c t i o n p r o p e r t i e s . A l so i d e n t i f i e d i n Tab l e 2 a r e t h e s t a n d a r d wind t u n n e l i n s t r u m e n t s and m e a s u r i n g t e c h n i q u e s used to d e f i n e such t e s t p a r a m e t e r s a s t h e mode l a t t i t u d e , t h e mode l s u r f a c e p r e s s u r e s , p r o b e p o s i t i o n s , and p r o b e m e a s u r e m e n t s . The f o l l o w i n g a d d i t i o n a l s p e c i a l i n s t r u m e n t a t i o n w a s . a l s o u sed i n s u p p o r t o f t h i s t e s t e f f o r t ,
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2.5.2 Model Surface Heat Transfer Measurements
Coaxial surface thermocouple gages were used to measure the model surface heating rates and surface temperatures. The coax gage consists of an electrically insulated Chromel~center enclosed in a cyllndrical Constantan sleeve. After assembly and installation in the model, the gage materials are blended together with a file creating thermal and electrlcal contact in a thin layer at the surface of the gage. The gage is used to monitor the surface temperature time history at a rate of 15 points per second. Assuming the surface thermocouple behaves as a homogeneous, one-dlmensional, semi-infinite solid, its temperature time history can be used to define the corresponding time history, of the incident heat flux. A complete description of this gage and the data reduction procedure can be found in Refs. 3 and 4. The recording and calibrating procedures for this type gage are summarized in Table 2.
2 5.3 .o -WlreAnemomotry . .
Flow fluctuation measurements were made using hot-wlre anemometry techniques. The constant-current hot-wire anemometer instrumentation vlth auxiliary electronic equipment was furnished by the VKF. The an- maometer current control (Philco-Ford Model ADP-13) which supplies the heating current to the s~nsor is capable of maintaining the current at any one of 15 preset levels individually selected using push-button switches. The anemometer amplifier (Philco-Ford Model ADP-12) which amplifies the wire-response signal contains the circuits required to electronically compensate the signal for thermal lag due to the finite heat capacity of the wire. A square-wave geDerator (Shaplro/Edwards Model G-50) was used in determining the time constant of the sensor whenever required. The sensor heating current and mean voltage were fed to autoranging digital voltmeters for a visual display of these parameters and to the VKF Bell and Howell model VR3700 B magnetic tape machine for recording. The sensor response a-~ voltage was fed to an oscilloscope for visual display of the raw signal and to a wave analyzer (Hewlett-Packard Model 8553B/8552B) for visual display of the spectra of the fluctuating signal and was recorded on magnetic tape for subsequent analysis by the VKF. A detailed description of the hot-wire anemometer instrumentation is given in Ref. 5.
The analog response signals from the hot-wire anemometer were Eecorded on the VKF Bell and Howell model VR3700 B magnetic tape machine in the FMmode. Each channel was calibrated and adjusted to have a slgnal-to-noise ratio of 35 db for a 1.000 volt rms output, The tape machine frequency response was +i to -3 db over a d-c frequency range to 500 kHz. In the present callbratlon, a sSne wave generator was used to check each channel at several discrete frequencies, using an rms- voltmeter which is periodically checked on i, 10, and i00 volt ranges. All magnetic tape recordings were made at a tape speed of 120 in./sec.
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3.0 TEST DESCRIPTION
3.1 TEST CONDITIONS AND PROCEDURES
- .
3.1.1 General
A summary of the'nomlnal test conditions Is given "below. "
M PT, p s i a TT~ °R PT2, p s t a P, p s i a RE/FT x 10 -6.
8.0 225 1350 1.91 0.023 1.0 580 ~ 4.92 0.060 2.5
A test summary showing all configurations tested and the variables for each Ispresented in Table 3.
In the'VKF continuous flow wind tunnels (A, B, C), the model is mounted on a sting support mechanism in an iinstallation tank directly underneath the tunnel test section. The tank is separated from the tunnel by a pair of fairing doors and a safety door. When closed, the fairing doors, except for a slot for the pitch sector, cover the opening to the tank and the safety door seals the tunnel from the tank area. After the model is prepared for a data run, the personnel access door to the installation tank is closed, the tank is vented to the tunnel flow, the safety and fairing doors are opened, and the model is injected into the alrstream, and the fairing doors are closed. After the data are obtalned, the model is retracted into the tank and the sequence is reversed with "the tank being vented to atmosphere to allow access to the model in preparation for thenext run. The sequence is repeated for each configuration change.
The probes were positioned during each'boundary layer survey along the normal to the model surface by an automatic stepping device which was programmed for step size and time duration.
3.1.2 Data Acquisition
A laminar boundary layer over the forward and n~tdportions of the body with transition beginning near the aft end was the desired operating eondltlon for the equilibrium wall temperature survey study. However, the boundary layer cov~litlon could only be determined for the cold wall case (TW/TT -- 0. 4) because of heat gage ]imitations. The cold wall boundary layer conditions were determined from heat-transfer rate distributions obtained with the coaxlal surface thermocouple gages. The model was injected into the tunnel flow and the heat gage output recorded continu- ously for approxlmately four (4) seconds. The model was then retracted -and cooled by flowing air over its surface to obtain a uniform wall temperature, near room temperature, prior to injection into the tunnel flow for the next run.
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As a result of the requirement to have laminar flow over most of the model's surface at a free-streamMach number of 8, the free-stream Reynolds number was varied depending on the blunt nose configuration. The shar~ configuration was tested at a free-stream Reynolds number of 1 .0 x I0 / f t , t h e 3% b l u n t n e s s a t 2 .5 x 1 0 6 / f t , and bo th t h e 10% and 40Z bluntness at 3.5 x I0 /ft, which is near the maximum operating conditions in VKF Tunnel B.
Surface pressure distribution data were obtained on each blunt nose configuration at the desired Mach number-ReTnolds number condition.
Plow 'field surveys were obtained only after the model had reached a state of temperature equilibrium. The model was positioned in a roll orientation (ROLL = -90 Deg) to avoid interference of the surface instrumentation on the flow field being surveyed.
Meanrfl~q.boundary layer profiles were obtained on the sharp and 3% bluntness configurations at six stations (approximately every 5 inches starting 5 inches from the base) using pitot pressure and total temper- ature probes. Similar mean flow profiles were obtained on the 40% bluntness configuration at mldbody and 5 inches from the base. The profiles extended from near the model~s surface to a helght of 2 to 3 6 (boundary layer thickness) In a direction normal to the surface. Generally a p cofile consisted of from 20 to 30 points located approxi- mately 0.010incbes apart. Measurements were recorded for processing by the data sFstem only after pressure stablizatlon had been achieved.
- Model wall pressure and temperature data were measured simultaneously w~th the probe data. Table 4 indicates the stations at which surveys were made on each configuration and relates station distance, X, to
surface distance.
The survey probe height relative to the model was monitored using a high-resolutlon (1224 lines/frame, 30 frames/sec) closed-clrcuit television (CCTV) system (~ig. 6). The camera was fitted with a tele~ scopic lens system which gave a magnification factor of 38 (from tunnel centerline to monitor picture). The probe and model were back-lighted using the collimated llght beam of the Tunnel B shadowgraph system which was aligned with respect to the model just prior to testing. Calibration of the system was made using a wire of 0,0095-in. diameter positioned at the test section centerl~ne. Subsequent measurements were made on the face of the monitor picture tube using scales specially prepared from the callbratlon images. The fleld of view was approximately 0.3 In. (axlally) by 0.2 In. (vertlcally) and a spacing of 0.001 in. was easily discernlble. The camera was isolated from tunnel vibrations by mounting it with the optics system which has a foundation separate from that of the tunnel. Small vibrations of the model were observable, and, using the calibrated viewing screen, it was possible to estimate the vertical motions of the model as being of the order of ±0.001 in. The probe vertical vibrations when present were estimated to be of the order of ±0.002 in. Positioning
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of the probe at a desired location (in terms of X) on the model, within the field of view of the CCTV system, was achieved using a gratlcule, marked in 0.1 in. increments of X and indicating a 0.1-1n. distance normal to the model surface. The graticule was viewed using the
Tunnul B shadowgraph system. 0,
'the primary t e s t t e c h n i q u e f o r the p r e s e n t i n v e s t i g a t i o n was h o t - wirt~ anemometry~ and c o n s i d e r a b l e e f f o r t was d i r e c t e d toward o b t a i n i n g q u a l i t a t [ v e and q u a n t i t a t i v e h o t - w i r e anemometer p r o f i l e d a t a . The mean boundary l a y e r p r o f i l e d a t a were n e c e s s a r y to d e f i n e the f l o w environment in the vicinity of the hotwire,
The hot-wlre anemometer profile surveys were of three general types: (i) continuous traverse surveys to map a particular region, (2) qualitatlve boundary layer profile surveys and (3) quantitative hot-wire data at particular point locations within a survey. "
To acquire data of the first category, with the hot-wire anemometer at a single sensitivity" (heating current), the probe was swept in a continuous manner from near the model's surface outward to a distance of approximately 2~. This type survey was nade on the sharp configuration at 28 stations starting near the aft end of the model and moving forward in approximately one-inch increments. Similar surveys were made on the 3Z bluntness configuration at 25 stations, the 10Z configurations at 2 stations, and at 3 stations on the 40% bluntness configuration. The r~ison for ~ewer profiles on the blunter configurations was the difficulty w|th survival of the hot-wlre probes in the blunt cone environment. Bused upon p~eyious experience, it is believed that the higher unit Reynolds number condition used for the blunt configuration was the principal factor in the wire'slc~csurvlval rate.
The hot-wire anemometer qualitative boundary layer profile data were obtained using a hot-wire anemometer probe and a total temperature probe. The general procedure was identical to the mean flow boundary layer profile sequence with the exception that much less time was needed for recording data at eat:h point in the profile (no stabilization time required as with the pitot pressure). This type of profile was made at selected model stations, generally at three-inch intervals along the model's surface, at a single wire sensitivity as the wire was traversed away from the model in increments of 0.010 inches.
The continuous-traverse surveys with the hot-wlre anemometer were generally characterized by a single peak in the plot of the anemometer response. The peak was defined as the location of the maximum distur- bance energy in the flow field at the given model axial station. At each of these peaks, quantitative hot-wlre data were taken by stepping through a sequence of 11 wire sensitivities.
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• Both the h o t - w l r e anemometer q u a l i t a t i v e bounda ry l a y e r p r o f i l e d a t a and the quantitative data at the maximum disturbance energy locations were recorded on magnetic tape at a tape speed of 120 in./sec.
A calibration of the recovery factor of the total temperature probe as a function of local Reynolds number was made in the free-stream flow of the Tunnel B test section. A Reynolds number variation was produced by varying PT while malntaing TT at a nomlnally:constant level. The free-stream total temperature was assumed equal to the measured stilling ch~imber temperature, TT. The range of Reynolds nmnher covered by a typical calibration and that required in the data reduction are shown Ln Fig. 7. The fairing shown in Fig. 7, a stralght-llne least-squares fit of the calibration data, was used for the data reduction eyrir the required range•
3.1.3 Hot-Wire Anemometer Probe Calibratiou
The evaluation of flow fluctuation measurements made using hot-wire anemometry techniques requires a knowledge of certain thermal and physic~l characterlsti~s of the wire sensor employed. In applications of the hot wire to wind tunnel tests by the ~KF, two complementary calibrations are used to evaluate the wire characteristics needed• The first cali- bration of each hot-wir~ probe is performed in the Instrumentation laboratory prior to the testing: the probe is placed in an oven and the reslstance of the wire is determined as a function of applied wire heating current at several oven temperatures between room temperature and 1000°F. The wire reference resistance at 32°F~ and the thermal coefficient of resistance~ also at 32°F, are obtained from the results~ and the wire aspect (length-to-dlameter) ratio is determined, using the wire res[stafice per unit length specified by the manufacturer with each supply of wire. Moreover, it has been found by the VKF that the exposure of the probes to the elevated temperatures of the oven cali- bration often serves to eliminate probes with. inherent weaknesses.
Each probe used for flow field measurements is calibrated in the wind tunnel free-stream flow to obtain the heat-loss coefficient (Nusselt number) and the temperature recovery factor characteristics of the wlre sensor as a function of local Reynolds number. The var- iations of Reynolds number in the free stream are obtained by varying the tunncl total pressure PT while holding the tunnel total temperature TT at a ~lominally constaDt level• The resulting relationships are expressed in equation form and are used to determine the values of the various wire sensitivity parameters required in the reduction of the quantitative measurements.
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3,'2- DATA REDUCT70N . . . .
The v a r i o u s t y p e s o f d a t a o b t a i n e d d u r i n g ~he t e s t e n t r y are • mummarized i n Tab le 3 . DATA TYPE c a l l o u t s u s e d are 2 , 3 , 4 , 6 , 9
~nd Heat Transfer. .
: ; A very limited quantity of hot-wlre anemometer measurements is ": tabulated in the data package accompanying this report. The only data .presented are the anemometer output rms voltage measured during the ;hot-wlre anemometer qualitative boundary layer profile series (DATA TYPE 3) and the free-sCream conditions used in the anemometer probe -calibrations (DATA TYPE 9). Hot-wire current'and mean voltage measurements are also given for the TYPE 9 data. The analysis of the
~-l-hot-wire anemometer data including modal and spectral analyses of the ] recorded signals is not included in the present report. ! . . . . . . . . . . . . . . . . . . J
The mean flow boundary layer data (DATA TYPE 4) includes an evaluation of several boundary layer parameters, namely: the boundary layer thickness, displacement thickness, and.momentum thickness. To determine these parameters requires a knowledge of the surface pressure and temperature at the survey station, the corrected total temperature measurement, a method for defining the boundary-layer edge, and the height relationship between the pltot and total temperature probes.
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The model surface pressures used in the boundary-layer calculations, which are tabulated in TYPES 3 and 4data results, were determined using a falrlng of the measured pressure distributions (TYPE 2 DATA) for the case of the 3Z ;bluntness configuration, and a fairing of measured pressure distributions extrapolated with the aid of theoretical solutions for regions where no pressure measurements were made for the Eemalnlng configurations. The static pressure across the boundary layer was assumed constant and equal to the surface value at each survey station. The surface pressure distributions used are shown £ n F i g . 8 .
The s u r f a c e t e m p e r a t u r e used was d e t e r m i n e d from the measured s u r f a c e t h e r m o c o u p l e da ta i n the v i c i n i t y o f the s u r v e y s t a t i o n . A t h r e e p o i n t Interpolation routine was used to calculate the wall temperature at the exact wall location using the nearest functioning thermocouples.
The hot-wire anemometer probe was located'0.125 in. to the right of the pltot probe (looking downstream with the picot probe in line wlth the model's vertical centerllne), and the total temperature probe was located 0.125 in. to the left. Allowance was made for this in determining the height of each probe off the model surface. Also, there was normally some misallgnment in the vertical direction, which was determined from the high resolution closed-clrcuit televlsionsystem during the test and verified after the test from photographs taken of
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the probes at the Inltial point of each survey. W i t h t h e s e cons ld - - :~ . , ~ ' . : • e r a t l o n s the h e i g h t s of the boundary-layer survey probes above the .--=
model s u r f a c e , in the d i r e c t i o n normal to the s u r f a c e , were c a l c u l a t e d for each p r o f i l e s t a t i o n and are g iven i n the t a b u l a t i o n s and p l o t t e d
. 7
data . " "
' I
• The boundary- layer surveys are •' tabula ted i n terms of the p l t o t pressure probe h e i g h t . The t o t a l temperature probe measurement corresponding to each p i t o t probe h e i g h t was determined us ing a t h r e e - po int i n t e r p o l a t i o n scheme. The c a l e u l a t l o n of l o c a l Reynolds number for use wi th the t o t a l temperature probe recovery f a c t o r c a l i b r a t i o n was i n i t i a t e ~ by us ing the uncorrected t o t a l temperature measurement then an i t e r a t i o n scheme fo l lowed u n t i l s u c c e s s i v e va lues of "corrected" ~ o t a l temperature were w i t h i n 0 . I deg R. For those surveys where the p l t o t probe was p o s i t i o n e d in the probe head s l i g h t l y lower than the t o t a l temperature probe ( c l o s e r to the model ) , the correc ted t o t a l temperature at the corresponding p l t o t h e i g h t s near the sur face w e r e determined from a. second order curve f i t us lng three p o i n t s , i . e . , the model sur face temperature and the correc ted t o t a l temperature at the f i r s t two probe h e i g h t s where i t was a v a i l a b l e .
The t h i c k n e s s of the model boundary layer on any g iven p r o f i l e was In ferred from the p r o f i l e o f the l o c a l uncorrected t o t a l temperature . va lue (TTLU). The boundary- layer surveys g e n e r a l l y extended w e l l b e y o n d the e s t imated boundary- layer t h i c k n e s s . - Uncorrected t o t a l temperatures measured above the boundary- layer edge ( i n t h e shock layer ) remained cons tant or e s s e n t i a l l y independent of the probe h e i g h t . The h e i g h t " " ' at which t h i s cons tant por t ion of the p r o f i l e began was d e f i n e d as the edge of the bo~qdary l a y e r . There was g e n e r a l l y a very d i s t i n c t , ,overshoot '~ in the uncorrected t o t a l temperature p r o f i l e j u s t p r i o r to the onset of the cons tant por t ion o£ the p r o f i l e . The p r o f i l e o f the v e l o c i t y r a t i o ( l o c a l v e l o c i t y - t o - v e l o c i t y at the edge) was then determined and the h e i g h t corresponding to a r a t i o of 0 .995 was found by i n t e r p o l a t i o n and a r b i t r a r i l y des ignated as the boundary- layer t o t a l t h i c k n e s s , DEL. Displacement and momentum t h i c k n e s s e s were determined by i n t e g r a t i o n u s i n g standard data r e d u c t i o ~ procedures .
3 . 3 UNCERTAINTY OF NF.ASUREMENTS
Zn genera l , in s t rumenta t ion c a l i b r a t i o n s and data u n c e r t a i n t y e s t i m o t e s were made u s i n g methods recognized by the N a t i o n a l Bureau of Standards (NBS), Ref . 6. Heasuremeut u n c e r t a i n t y (U) i s a combination o£ b ia s and p r e c i s i o n errors de f ined as:
= ~ .
• , , . - . .
u = ± ( s + t95s)
"-where B i s tl~e b ias l i m i t , S i s the-s~n'p-ie standard d e v i a t i o n , and t95 £s the 95th percentile point for the two-tailed Student's "t" distribution, which for degrees of freedom grea ter than 30 equals 2.
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Estimates" o f the measured data u n c e r t a i n t i e s f o r t h i s t e s t , i n c l u d i n g the b a s i c h o t - w i r e anemometer measurements i n c l u d e d in t h i s r e p o r t , are g i v e n in Table 2a, b. E s t i m a t e s o f u n c e r t a i n t i e s in f l o w f l u c t u a t i o n s
, d e r i v e d from the h o t - w l r e anemometer measurements and in o t h e r c a l c u l a t e d f l o w survey parameters f a l l o u t s i d e t h e scope o f t h i s p r o j e c t e f f o r t . I n ' g e n e r a l , measurement u n c e r t a i n t i e s are determined from I n - p l a c e c a l i - b r a t l o n s through the data r e c o r d i n g sys tem and data r e d u c t i o n program.
...... The p r o p a g a t i o n o f the e s t i m a t e d b i a s and p r e c i s i o n e r r o r s o f the measured data through the data r e d u c t i o n and a n a l y s i s w a s made in accordance w i t h R e f . 6 , and i s summarized i n Table 2c .
. . . . . . . . . . . 4 . 0 .DATA PACKAGE PRESENTATION
B o u n d a r y - l a y e r p r o f i l e d a t a , model s u r f a c e da ta , probe c a l i b r a t i o n d a t a , and b a s i c h o t - w i r e anemometer data from the t e s t were redQced to t a b u l a r a n d . g r a p h i c a l form f o r p r e s e n t a t i o n as a Data Package . Examples
. _ o f the b a s i c data type t a b u l a t i o n s a r e f i h o w n i n Appendix I I I .
= I l l u s t r a t i o n s o f the hea t t r a n s f e r • r a t e d i s t r i b u t i o n data and the . q ~ m l i t a t i v e h o t - w i r e anemometer p r o f i l e r e s u l t s are shown in P i g s . 9 and
"10 , r e s p e c t i v e l y . FigUre 11 i s an example o f the mean f l o w boundary- ~ '~ layer survey r e s u l t s f o r the 10% b l u n t n e s s c o n f i g u r a t i o n a t a p a r t i c u l a r .... survey s t a t i o n . The t a b u l a t i o n s i n the appendix correspond to t h e s e
p l o t t e d data . • - . . - . . . - . . . . . . . . - : - -
" . ' - 'L . . . . . . . . . . . . . . . . . " . . . . . . ~ ' ~ - - • : - ' - " . . . . . . : " ~ - " : . . . . . . " - : : " ° . . . . : "
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• ' , / - , . " . . . . . ' . , ~ , - , ~ , ~ ' ~ . - . , • ,
;." . . . . . . ~ - - - . ~ . . . . - ' ~ - ~ " - $ . 0 .REFERENCES "- ; . . . . . . '
:1~ Test F a c i l i t i e s Handbook (Eleventh E d i t i o n ) . "Von K~rm~n Gas Dynamics " Fac£1~y, Vol. 3." Arnold Eng~neerlng Development Center, June 1979.
2. Doughman, E. L. '°Development of HoC Wire Anemometer for Hypersonlc ,. '" Turbulent Flows," Ph~Ico-Ford Corpora~on'Publlcaclon No. U-4944,'-.
December 1971; and The Review of Sclent~flc Instruments, Vol. 43,-. - No. 8, August 1972, pp. 1200-1202.
3 . Trimmer, L. L . , e~ a l . '~easuremenCs of Aerodynamic HeaC Races ac the AEDC Von K~rm~n F a c i l l C y , " Reprint from ICIASF ~973 Record, InCernaCional Congress on InscrumenCaClon on Aerospace S imula t ion Facil~les, September 1973.
4, . Cook, W. 3 . and Felderman, E. 3. "Reduction of Data from Th~n-F~im . . . . . Beat Transfer Gages: A Concise Numerical Technique," AIAA Journal =" Vol. 4,'No. 3, March 1966, p. 561.
5. Donaldson, J. C., Nelson, C. G., and OSHare, J. E. "The Development of Hot Wire Anemometer Test CapabillCles for Mm = 6 and M® = 8 AppllcaC±ons," AEDC-TR-76-88 (AD A029570), September 1976.
• Zhompson, J. %a"dbook Vncercalncy in Gas T,rblne Maasure- . . . . m e n e s , " A E D C - T R - 7 3 - 5 ( A D 7 5 5 3 5 6 ) , F e b r u a r y 1 9 7 3 .
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APPENDIX II.
TABLES
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