W IS020 CALSPAN F1ELD SERVICES INC ARNOLD AFS TN AgOC DIV F/6 22/2NASA/ROCKWELL INTERNATIONAL SPACE SHUITTLE ORBITER ABOPT t#ATINB--ETC CUl

r, UwW-7LASS-,,EDNOV &I L A TICATCH, K W UT I AJTR6-V6

O N IFE

ECS-B-3

Hill II*~L 111 1.Q_I..0

mill,

111111.25 1 .4

MICROCOPY RESOLUTION TEST CHARTNATIONAL BUREAU Of S ANDARDS 1963 A

AEDC-TSR-81-V36

NASA/ROCKWELL INTERNATIONAL SPACE SHUTTLE

ORBITER ABORT HEATING TEST (OH-ill)

~ L. A. Ticatch and K. W. Nutt

_____Caispan Field Services, Inc.

Novemiber 1981

Final Report for Period September.25-30, 1981

* Approved for public releese distribution unlimited.

DTrI CELECTE

JUNO 2198t

ARNOLD ENGINEERING DEVELOPMENT CENTERARNOLD AIR FORCE STATION, TENNESSEE

AIR FORCE SYSTEMS COMMANDUNITED STATES AIR FORCE

82 06 01 177

T"

NOTICES

When U. S. Government drawing, specifications, or other data are used for any purpose otherthan a definitely related Government procurement operation, the Government thereby incus noresponsibility not any obligation whatsoever, and the fact that the Government may haveformulated, furnished, or in any way supplied the said drawings, specifications, or other data, isnot to be regarded by implication or otherwise, or in any manner licensing the holder or anyother person or corporation, or conveying any rights or permission to manufacture, use, or sellmy patented invention that may in any way be related thereto.

References to named commercial products in this report are not to be considered in any senseas an endorsement of the product by the United States Air Force or the Government.

This report has been reviewed by the Office of Public Affairs (PA) and is releasable to the NationalTechnical Information Service (NTIS). At NTIS, it will be available to the general public, includingforeign nations.

APPROVAL STATEMENT

This report has been reviewed and approved.

J. T. BESTAeronautical Syst -.as BranchDeputy for Operations

* Approved for publication:

FOR THE COMMANDER

r mo atp , :rrctorrospace Flight Dynamics Test

leputy for Operations

I I_________________________

UNCLASSIFIED ____

SECURITY CLASSIFICATION OF THIS PAGE (When Data FInt'red)

REPORT DOCUMENTATION PAGE READ INSTRUCTIONS1. REPORT NUMBER 2. GOVT ACCESSION NO. 3. RECIPIENT'S CATALOG NUMBER

AEDC-TSR-81-V36

4. TITLE (and Subtitle) S. TYPE OF REPORT & PERIOD COVERED

NASA/ROCKWELL INTERNATIONAL SPACE SHUTTLE Final Report

ORBITER ABORT HEATING TEST (OH-111) September 25-30, 19816. PERFORMING O1G. REPORT NUMBER

7. AUTHOR(&) S. CONTRACT OR GRANT NUMBER(s)

L. A. Ticatch and K. W. Nutt, Calspan FieldServices, Inc./AEDC Division

9. PERFORMING ORGANIZATION NAME AND ADDRESS 10. PROGRAM ELEMENT. PROJECT. TASKAREA & WORK UNIT NUMBERSArnold Engineering Development Center Program Element 921E01

Air Force Systems Command Control No. 9E01Arnold Air Force Station, TN 37389

!I. CONTROLLING OFFICE NAME AND ADDRESS 12. REPORT DATEJohnson Space Center (NASA-JSC(ES3)) November 1981Houston, Texas 77058 13. NUMBER OF PAGES

5314. MONITORING AGENCY NAME & ADDRESS(if different from Controlling Office) IS. SECURITY CLASS. (of this report)

UNCLASSIFIED

15a. DECLASSIFICATION/DOWNGRADINGSCHEDULE N/A

16. DISTRIBUTION STATEMENT (of this Report)

Approved for public release; distribution unlimited.

17. DISTRIBUTION STATEMENT (of the abstract entered in Block 20, if different from Report)

IS. SUPPLEMENTARY NOTES

Available in Defense Technical Information Center (DTIC).

19. KEY WORDS (Continue on reverse side if necessary and identify by block number)

heat transferthin skinspace shuttle orbiterhypersonic testing

20. ABSTRACT (Continue on reverse side If necessary end Identify by block number)

Thin-skin thermocouple heat transfer tests were conducted on two 0.0175 scaleand one 0.04 scale models of the Space Shuttle orbiter at attitudes that wouldbe encountered in a transatlantic abort maneuver. The model angles of attackranged from 40 to 55 degrees with yaw angle varying from -2 to 2 degrees. Datawere obtained at Mach 8 in the AEDC-VKF Hypersonic Wind Tunnel B at free-stream Reynolds numbers ranging from 0.5 x Tu/ to 1.5 x 106 per foot.

DD I FAN"73 1473 EDITION OF I NOV 65 IS OBSOLETE UNCLASSIFIEDSECURITY CLASSIFICATION OF THIS PAGE (When Date Entered)

: .4

CONTENTS

Page

NOMENCLATURE ......... ........................ 31.0 INTRODUCTION ........... ....................... 62.0 APPARATUS

2.1 Test Facility .......... .................... 62.2 Test Articles .......... .................... 72.3 Test Instrumentation

2.3.1 Test Conditions ........... ........ 72.3.2 Test Data .......................... 8

3.0 TEST DESCRIPTION3.1 Test Conditions ... ....... . ............ 83.2 Test Procedure

3.2.1 General ......... ................... 83.2.2 Thin-Skin Thermocouple ...... ............ 93.2.3 Oil-Flow ......... ... .............. 9

3.3 Data Reduction3.3.1 Thin-Skin Thermocouple Data ............ 9

3.4 Uncertainty of Measurements ... ............. ... 114.0 DATA PACKAGE PRESENTATION ..... ................ ... 12

REFERENCES .... .................. .......... . 12

APPENDIXES

I. ILLUSTRATIONS

Figure

1. Tunnel B ......... ......................... .... 142. Installation Photograph of 60-0 Model .. .......... ... 153. 60-0 Model Installation ................. 164. Basic Dimensions and Coordinate System for the 0.0175 *

Scale Orbiter Models ....... .................. .. 175. Installation Photograph of 56-0 Model ........... 186. 56-0 Model Installation .. 197. Installation Photograph of 83-0 Model .......... 208. 83-0 Model Installation ..... ................. ... 219. Basic Dimensions and Coordinate System for the 83-0 Model 22

10. Thermocouple Locations on 60-0 Model .. .......... . 2311. Thermocouple Locations on 56-0 Model .. .......... . 2912. Thermocouple Locations on 83-0 Model .. ............. 30

* 13. Thin-Skin Thermocouple Plotted Data .. ........... ... 3414. Oil-Flow Photographs on 60-0 Model (Run 262) ...... . 35

II. TABLES

Table

1. Data Transmittal Summary ................ 37

2. Estimated Uncertainties . . . . .......... .. 38

3. 60-0 Model Thermocouple Coordinates . . . . . . . . . .. 40

4. 56-0 Model Thermocouple Coordinates . . . . . . . . . .. 43

14I

Page

5. 83-0 Model Thermocouple Coordinates .. .. ........ 446. Test Data Summary. .. ...................7. Photographic Summary .. ................... 50

III REFERENCE HEAT-TRANSFER COEFFICIENTS. .. ........... 51

IV SAMPLE TABULATED DATA

1. Thin-Skin Thermocouple Tabulated Data. .. .......... 53

rAccession

For

DTIC TABiA AUnannouncedJustification E

Distribution/

AvailaLc41itY Codes

'Avail-adoDit Special 1

2

NOMENCLATURE

ALPI Indicated pitch angle, deg

ALPHA Angle of attack, deg

ALPPB Prebend angle, deg

b Model skin thickness, in.

B Wing span, in. (see Fig. 4)

BV Height of model vertical tail, in. (see Fig. 4)

c Model material specific heat, Btu/lbm-*R

C Local chord of wing or vertical tail, in. (see Fig. 4)

DELTAE Elevon deflection angle, deg

DELTASB Speed brake deflection angle, deg

DELTBF Body flap deflection angle, deg

DTW/DT Derivative of the model wall temperature

with respect to time, 0R/sec

H(REF) Reference heat transfer coefficient (seeAppendix III)

H(TR), H(TT) Heat-transfer coefficient based on recoveryH(O.9TT), H(O.85TT) temperature, TR (TR = TT, O.9TT, or 0.85TT assumed

for these data), QDOT/(TR-TW), Btu/ft2-sec-*R

L Reference length, in. (see Fig. 4).

rM, MACH NO. Free-stream Mach number

MU Dynamic viscosity based on free-stream

temperature, lbf-sec/ft2

I!3

MUTT Dynamic viscosity based on TT,lbf-sec/ft2

P Free-stream static pressure, psia

PT Tunnel stilling chamber pressure, psia

PT2 Stagnation pressure downstream of a normal shock,psia

PHI Radial angle location of thermocouple in modelcoordinates, deg (see Figs. 4 and 9)

PHI1 Indicated roll angle, deg

Q Free-stream dynamic pressure, psia

QDOT Heat-transfer rate, Btu/ft -sec

RE Fr-e-stream unit Reynolds number, ft-

-3RHO Free-stream density, lbm/ft

RN Reference nose radius, (0.0175 ft or 0.04 ft,determined by model scale)

RUN Data set identification number

STFR Stanton number based on reference conditions(see Appendix III)

T Free-stream static temperature, OR

TC NO Thermocouple identification number

TIME Elapsed time from lift-off, see

TR Assumed recovery temperature, OR

TT Tunnel stilling chamber temperature, OR

TW Model surface temperature, *R

V Free-stream velocity, ft/sec

X Model scale axial coordinate from model nose or

leading edge of wing or vertical tail (see Fig.

4 and 9) in.

XO Full scale axial coordinate from a point 235 in.ahead of the orbiter nose (see Fig. 9), in.

Y Model scale lateral coordinate (see Fig. 4), in.

YAW Yaw angle of model, deg

YO Full scale lateral coordinate, in.

Z Model scale vertical coordinate (see Fig. 4), in.

ZO Full scale vertical coordinate, in.

P Model material density, ibm/ft3

.1

-1

5

1.0 INTRODUCTION

The work reported herein was performed by the Arnold Engineering

Development Center (AEDC), Air Force Systems Command (AFSC), underProgram Element 921E01, Control Number 9E01, at the request of theJohnson Space Center (NASA-JSC(ES3)), Houston,Texas. The NASA-JSC (ES3)

program manager was Mrs. Dorothy B. Lee and the Rockwell International

project engineers were Mr. C. L. Berthold and Mr. J. Gee. The resultswere obtained by Calspan Field Services, Inc./AEDC Division, operatin,contractor for the Aerospace Flight Dynamics testing effort at the '.z'DC,AFSC, Arnold Air Force Station, Tennessee. The tests were perfor-.ed inthe von Karman Gas Dynamics Facility (VKF), under AEDC Project No. C628VB.

The test was performed in the 50-ii.-diam Hypersonic Wind Tunnel(B) at the von Karman Gas Dynamics Facility (VKF) during the periodSeptember 25, 1981 to September 30, 1981. Data were recorded at Mach

number 8 for nominal Reynolds numbers ranging from 0.5 x 106 to 1.5 x106 per foot. The nominal model angles of attack ranged from 40 to 55degrees with model yaw angles varying from -2 to 2 degrees. All thin-skin thermocouple data were obtained from three space shuttle orbitermodels designated 56-0, 60-0, and 83-0.

The test had a NASA/Rockwell designation of OH-111. The testobjective was to obtain thin-skin heat transfer data on the spaceshuttle orbiter model at attitudes that would be encountered in atransatlantic abort maneuver.

A summary of the test data transmitted is shown in Table 1.Inquiries to obtain copies of the test data should be directed toNASA-JSC (ES3), Houston, Texas 77058. A microfilm record has beenretained in the VKF at AEDC.

2.0 APPARATUS

2.1 TEST FACILITY

Tunnel B (Fig. 1), is a closed circuit hypersonic wind tunnelwith a 50-in. diam test section. Two axisymmetric contoured nozzlesare available to provide Mach numbers of 6 and 8 and the tunnel may

be operated continuously over a range of pressure levels from 20 to300 psia at Mach number 6, and 50 to 900 psia at Mach number 8, withair 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 cooledby integral, external water jackets. The tunnel is equipped with amodel injection system, which allows removal of the model from the testsection while the tunnel remains in operation. A description of thetunnel may be found in Ref. 1.

6b.

2.2 TEST ARTICLES

Three Space Shuttle orbiter models were used to obtain the thin-skin thermocouple data for this test. Two of the test articles were0.0175 scale models of the full orbiter and were designated as the60-0 and 56-0 models. The third model was a 0.04 scale of the fronthalf of the orbiter and was identified as the 83-0 model. All of themodels were supplied by Rockwell International.

The 60-0 model was a 0.0175 scale thin-skin thermocouple model ofthe Rockwell International Vehicle 5 configuration. The model was con-structed of 17-4 PH stainless steel with a nominal skin thickness of0.030 in. at the instrumented areas. All thermocouples were spot weldedto the thin-skin inner surface.

A photograph of the 60-0 model injected in the tunnel is shownin Fig. 2. A sketch of the 60-0 model installation in the tunnel isshown in Fig. 3. The basic dimensions and coordinate definitions forthe 0.0175 scale models are shown in the sketch presented in Fig. 4.The deflection angles of the speedbrake, elevons, and body flaps wereall set at zero throughout the test.

The 56-0 model used for this test was model number 2B of thematerial "LH" 56-0 phase change paint model series. This was a 0.0175scale model with the same external contour as the 60-0 model. Thepilot side of the fuselage consisted of a thin-skin thermocouple insertcontoured to the vehicle lines. This insert was constructed of 17-4stainless steel with a nominal skin thickness of 0.020 in. at thethermocouple locations. A photograph of the 56-0 model injected inthe tunnel is shown in Fig. 5. A sketch of the 56-0 model installationis shown in Fig. 6. The dimensions and coordinate system presented inFig. 4 also apply to the 0.0175 scale 56-0 model.

The 83-0 model was a 0.04 scale model of the forward half of theorbiter. This model was also constructed of 17-4 PH stainless steelwith a nominal skin thickness of 0.030 in. A photograph of the 83-0model in the installation tank beneath the test section is shown in Fig.

47. The installation sketch of the 83-0 model is shown in Fig. 8 andthe coordinate system and basic dimensions for the 83-0 model arepresented in Fig. 9.

2.3 TEST INSTRUMENTATION

2.3.1 Test Conditions

The instrumentation, recording devices, and calibration methodsused to measure the primary tunnel and test data parameters are listedin Table 2a along with the estimated measurement uncertainties. Therange and estimated uncertainties for primary parameters that were cal-culated from the measured parameters are listed in Table 2b.

7

2.3.2 Test Data

The 60-0 model was instrumented with 600 thirty-gauge iron-constantan

and Chromel®-constantan thermocouples. Only 250 of these thermocouples

were used on this test. Thermocouple locations for this model are

presented in Fig. 10; the dimensional locations and skin thickness for

the thermocouples connected on this test are listed in Table 3. Thethermocouples identified by a number only are iron-constantan. The

thermocouples identified by a number followed by the letter A or C are

Chromel-constantan that were added to the model. The letter D after a

thermocouple number designates an iron-constantan thermocouple in a new

location on the OMS pod.

The 56-0 model instrumentation consisted of 80 thirty-gauge Chromel-

constantan thermocouples located on the thin skin insert. All of these

thermocouples were connected on this test. The thermocouple locations

for this model are presented in Fig. 11. The dimensional locations

and skin thicknesses are listed in Table 4.

For this test only 250 of the 482 thirty-gauge Chromel-constantanthermocouples on the 83-0 model were connected. The thermocouple loca-

tions for this model are illustrated in Fig. 12. The dimensionallocations and skin thicknesses for the thermocouples used on this

test are listed in Table 5.

3.0 TEST DESCRIPTION

3.1 TEST CONDITIONS

A summary of the nominal test conditions at each Mach number is

given below:

M PT, psia TT, OR Q, psia P, psia RE x 10- 6 , ft- 1

8 100 1250 0.5 0.010 0.58 205 1250 1.0 0.02 1.08 .325 1300 1.5 0.035 1.5

A test summary showing the configurations tested and the variables

for each is presented in Table 6.

3.2 TEST PROCEDURE

3.2.1 General

In the VKF continuous flow wind tunnels (A, B, C), the model is

mounted on a sting support mechanism in an installation 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 openingto the Lank 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

8

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 airstream. After the data are obtained, the model is retracted into

the tank and the sequence is reversed with the tank being vented toatmosphere to allow access to the model in preparation for the next run.

A given injection cycle is termed a run, and all the data obtained are

identified in the data tabulations by a run number.

3.2.2 Thin-Skin Thermocouple

Prior to each test run, the model temperatures were monitored toensure that the model was nominally isothermal. The model was then in-jected at the desired test attitude as the data acquisition sequencecommenced. The model remained on the tunnel centerline for about threeseconds and was then retracted into the installation tank. The modelwas then cooled while being repositioned for the next injection.

A 256 channel multiplexing analog-to-digital converter was used inconjunction with a Digital Equipment Corporation (DEC) PDP-11 computerand a DEC-10 computer to record the temperature data. The system sampledthe output of each thermocouple approximately .13 times per second.

3.2.3 Oil-Flow

Oil-flow testing was done on the 60-0 model and the 83-0 model.For oil-flow testing the models were painted black for contrast, andin general, a white oil with a viscosity of 25 centistokes was appliedto the surface with a sponge for each run. The oil was applied dif-ferently on the first two runs of the 83-0 model. On runs 77 and 78,coatings of 800-centistoke and 200-centistoke white oil were appliedover a coating of clear Dow Corning oil with a viscosity of 100

centistokes. The model was positioned to the test attitude and in-jected into the tunnel flow for about 20 sec. During this time, fourstill cameras photographed the model at 2-second intervals. Locotionsof the cameras and camera numbers are specified in Table 7. After themodel was retracted from the tunnel flow, it was cooled and cleanedbefore oil was reapplied for the next test run. Oil flow runs arespecified in the Test Data Summary, Table 6.

3.3 DATA REDUCTION

3.3.1 Thin-Skin Thermocouple Data

The reduction of thin skin temperature data to coefficient form

normally involves only the calorimeter heat balance for the thin skinas follows:

QDOT - pbc DTW/DT (1)

H(TR) = QDOT = pbc DTW/DT (2)TR-TW TR-TW

Thermal radiation and heat conduction effects on the thin-skinelement are neglected in the above relationship and the skin temperature

9

response is assumed to be due to convective heating only. It can beshown that for constant TR, the following relationship is true:

d n TR-TI _ DTW/DT (3)Tt_ R-TW TR-TW

Substituting Eq. (3) in Eq. (2) and rearranging terms yields:

H(TR) = d in [TR-TI (4)pbc dt TRTW

By assuming that the value of H(TR)/pbc is a constant, one can seethat the derivative (or slope) must also be constant. Hence, the term

in tTRTI]

is linear with time. This linearity assumes i:he validity of Eq. (2)which applies for convective heating only. The evaluation of conductioneffects will be discussed later.

The assumption that H(TR) ard c are constant are reasonable for thistest although small variations do occur in these parameters. The varia-tions of H(TR) caused by changing wall temperature and by transitionmovement with wall temperature are trivial for the small wall temperaturechanges that occur during data reduction. The value of the model materialspecific heat, c, was computed by the relation

c = 0.0797 + (5.556 x 10- 5)TW (17-4 PH stainless steel) (5)

The maximum variation of c over any curve fit was less than 1.5 percent.Thus, the assumption of constant c used to derive Equation 4 was reason-

able. The value of density used for the 17-4 PH stainless steel skinwas p = 490 lbm/ft3 , and the skin thickness, b, for each thermocoupleis listed in Tables 3, 4 or 5.

The right side of Equation 4 was evaluated using a linear least

L- squares curve fit of 15 consecutive data points to determine the slope.

The curve [it was started at approximately the time the model arrivedon the tunnel centerline. For each thermocouple the tabulated value ofH(TR) was calculated from the slope and the appropriate values of pbc;

' i.e.,

d [T-T lH(TR) pbc d [ in [TR-TW (6)

10

To investigate conduction effects a second value of H(TR) was calculated

at a time one second later. A comparison of these two values was usedto identify those thermocouples that were influenced by significant con-

duction (or system noise). The data for a given thermocouple were deleted*if these values of H(TR) differed by more than 35 percent. In general,

conduction and/or noise effects were found to be negligible.

Since the value of TR is not known at each thermocouple locationit has become standard procedure to use three assumed values of TR.The assumed values are 1.OTT, 0.9TT and 0.85TT. The use of theseassumed values of TR provides an indication of the sensitivity of theheat-transfer coefficients to the value of TR assumed. As can be

noted in the tabulated data, there are large percentage differencesin the values of the heat-transfer coefficients calculated from thethree assumed values. Therefore, if the data are to be used forflight predictions, the value selected for TR is obviously very

important and is a function of model location and boundary layerstate.

The heat-transfer coefficient calculated from Eq. 4 was normalized

using the Fay-Riddell stagnation point coefficient, H(REF), based on anose radius of 1.0 ft full scale (see Appendix III). The referencenose radius, RN, used to calculate H(REF) is either 0.0175 ft or 0.04ft as determined by the model scale.

3.4 UNCERTAINTY OF MEASUREMENTS

In general, instrumentation calibrations and data uncertaintyestimates were made using methods recognized by the National Bureau of

Standards (NBS). Measurement uncertainty is a combination of bias andprecision errors defined as:

U = ± (B = t 9 5S )

where B is the bias limit, S is the sample standard deviation and t?5 isthe 95th percentile point for the two-tailed Student's "t" distribu ion(95-percent confidence interval), which for sample sizes greater than 30

is taken equal to 2.

Estimates of the measured data uncertainties for this test aregiven in Table 2a. The data uncertainties for the measurements are

determined from in-place calibrations through the data recording systemand data reduction program.

* Propagation of the bias and precision errors of measured data

through the calculated data was made in accordance with Ref. 2 and

the results are given in Table 2b.

?*

The word DELETE is used on the tabulated data to identify these thermo-

couples.

4.0 DATA PACKAGE PRESENTATION

Heat-transfer coefficients were obtained at selected :ocations onthe 56-0, 60-0, and 83-0 models of the space shuttle orbiter. Sampletabulated data are presented in Appendix IV.

Representative data from the upper centerline (PHI = 180 deg) ofthe 83-0 model are presented in Fig. 13. Data from two runs are pre-sented as a sample of data repeatability.

Representative oil-flow data of the 60-0 model are shown in Fig.14.

REFERENCES

1. Test Facilities Handboc], (Eleventh Edition). "von Karman GasDynamics Facility, Vol. 3." Arnold Engineering Development Center,June 1979.

2. Thompson, J. W. and Abernethy, R. B. et al. "Handbook Uncertaintyin Gas Turbine Measurements." AEDC-TR-73-5 (AD755356), February1973.

1

12

APPENDIX I

ILLUSTRATIONS

1 13

Screen ~ ~ ~~ b Tunneln NozeScinTest Sect ionifuerScto

OeaigF ig. Tant Tunnel en

ILWI

I

L116L

0C)

'-1

0 c

-f-4

1-44

00

IDr

(116

CA

00-0 00

U) 4

'-44

4 I4

'00.A-4

gooC--4

P4 410 I03

0 0 0

0 44

r O

U):1n

000

17 C

H II

S1 cc~

C

IC

C

V

18

co

0 a

01-4

4J a

I00

00

I e.J

x 001

VI

I7

I2

a)o _ v j

-S-o

o) Co

00

-4-

J-o

0

U)

. ......

0)P4 4

04J

41

o 4)

00 0

0

41

cnn

C4J

220

0

rq 0)

*In 0

0) (A-40

0

23 4U

00

rI C-,

TO a0 0 = o

ate(Y - )IT) u**

g2.~~~1 12, ..- *

0

24

44

00

qN44

VIAI

\34 \bNo )'1

IB

25s.

t.1 W

ON c~IN < <

044

4,9

ONN

N 00<~ .

InI

4

N

00

-i - -. -C - - -- --

60,

ec, Q

-. "~Q r-~ - *et:

0 00~

a)

020

oInN 44

< 4-

- - - - - - - - -

I' r27

a OD 0 0O

0% 00

0~0

00 o(NJ

cu0 00

'a ~ca -

0 0 c 0

N o

-.000

-.0 r 0

'NJY m "

0 ~~J 90

28 NJ C

0 0

* 0 0

4

_.* . .

290

000

00.

-0 -0 j

0177 178 25

79

3 '

0 2Z. 2 I 2 3183 00

123+ _6 2 329'r- 6i e S62 7

22- 3230

0 97 20 !2100 2P7 0

002~ 20

0

--- --- -

00

4Cd

r 9 . 61,Z **no8

.9 z

0

4

0)

0 0

C4

C1 uI E 0 C,4

0

E-4~ -

0 0

-----------

31~

Forward Facin; Upward Facing

RCS Nozzles RCS Nozzle (Typ)

Center79 382 384 (cfii 38 5 386 387..... C- -- e ...... -e ... *(F +- e.......----

~161 162 16X.!/ 164 165 166

0 ® 0 0 0167 168 169 170 171 172 Pilots

_______-'-)- - - 0

- ...... ~r. '_

173 174 175 176

Enlargement

Nose View of-.--- ?A83-0 Model

'477 45051

Enlargement .29\3

474 449

303473 2

'7 * 281 (X/l,=0.025)

287(X/L=0.05)

290(X/L=0.2)

Centerline

c. Thermocouple Locations on Upper RCS Nozzles and

Lower Fuselage

Figure 12. Continued

32

*1!

CEl)

44

g. V

-HlIn

'-4

C4.

333

:j-4 0

V3 -r40 OD0o r-4-.H

Cl 0 0 -4r0 z w

0-I I~

En c

'~CC

IEM-ViI

oo ~~ ~ ~ ~ ~ ~ ~ ~ d I-DM-- n Cj1 0 o.: 3, c 10L n

34l

ConitRn:e = 8.x0 6 t

I Camera 3

Fitguro 1. Oil-Flow Photographs on n3O-O Model (Run 2632)

APPENDIX II

TABLES

36

to V

I I .0.

-0 0

-II

4 '

06

~0

1:1 1, 04 ; .4

a . 4.1) 0

'N 1( C) 0

I.. 0

0 Ccf O C'J 4 cl M

C. h

W %4

69 0

11) 4.

00 W

:a z .- o' A

0) 0

.4 Il 4

w 06N600

V 'AO CIO C

-C =l tav C -Cr4.. C- Q 94 a4 a

C, to "

A 0 400 '

4.,0

00 0 M L1 QA -4.4 'A.. C , " 2' C, , m -0

0 o9o 0 -

- 0 'n4

o0 ,,Cc 04-3 410. 0.;_ 2 4) -3

0~.u 0 L40 C, r2 S..-5'uo 0) 04) .. 0 0 0

> Id-. 4)4c4a(I m~C# 4 0) J.4

0w. 0Al. 0 41

4 44) bo v

CA). +4 rs r

00 0-4 v: ) 004 0

41.4). CO 00 .4 4

> > 0 443 @0 D0.

0 Q r v 0 000

0~~ 0 4(0 .--. 0 T.4 R4 u ) 0

.44 F.

0. S.2 0- c.U) 0.C4,)

4 00' rI0 4 4 0 09:0 0l 0. ~,~'

vi ua - 00r

010 C1 MC U.aA0a

E-' ~~ ~C T34 0 u~o 1J 00

e'J w l u o 0l w 410

0, W -

44) Q,-. 0

r_ ZI~ In JO llu 0~ 0

a) P5

T~ 0 o 0 C 0 0 q 0V

~4 +I

st] ua u bo

r An

w 0 00 + 44 4 -4-

C4)

An U/22f -r

__ _ _ .0

t x*w ) .N

Ma '

141100 0x x 00

0 01

,a, 110 If 1co. adlwllj0

L1 O

CA 0

V 00 00~,+, 0.-4 0 0+0,+

r. P4 DI

4) ua3.ad *? c 1

C4 ,-(.-4' 0

-4 04 C

W w0* I I

,v r- -a nuI oc

jo 41ur

0-

o o

w. 14 la~ d c?. 'o

N 4) 0) u.

00 0

0 4

0)0')d u) H04

to - u

4 0.0. .to

39

C 0 W0I~ 6 C, 0.Qr MW ~ 4 M mt.1 N 41 N 0 NClelMN Nfl ~ Cl 4C. M. N(NO 4NNNa00 00 0 0 000 cc00C 0 00 00 00

.0

to U" cl C4 w. Lo U ) 00 4)04) al~ 4 ~. ~

m C- V4 . 0 '0 to*4 N w 0 . el "I to . 0 0 Ch 4 a, .0 C Mv 6 .l. . q .~ v I to0 0 to n ul -'% 10 to to

'o -V _ ___t ___vl0 -

0. , N N N m M 0I 0 CO.)4 N 0N 0C C-3O

^ I M. V 05 C N m m1 .- C40 e N 4 C44 ..iC OW " N mC! C!0 C! C ! 'C0 a 00 0 a0 0 0 0 4 0 .6 C 1 0 60 a

o ~ ~ ~ ~ ~ ~ ~ -o to -. C). V~NN ~ 0 . 3 4) . ~ N C ' 4 O ~

.4 'n C4 C444 t4 c 4c n m a r w m m 4

o 44 DN 0 ')o V C.0 0

00 0 0 000 0 0 0 0 0 0 0

M3 k^ M 0? -' N~ - m 0 - 0 .4 0 ca

0 ' 0 0 0 4 4C' 5. 0 0 co 0 .4 0W C4 C4 -N OD4

C4 4 4)4 w.N0" N V(0 .4 0 w 00w-m 0 w o0 w0(Ce0 0N40 0 0 4. iC4 C40.) m r) mC17 M m m

0

N)6( mN N N0 N 0 ( 41 6 1 0 4 0 '

o~~ -.. . . -C N -4( N N N 41111')4 ~ 41

000 00 0 0 0 0 0 0 0 0 0 0

'43 0

0 0 4 0 4 0 4 0 0 N

ob 0 a * 0 0 0 a

0 00000000 4 4 00a

U 4.

(Irv

.40

C~~~~ 4040 Q C~ (140 0 040 J . (f0

04 000 C' CO~ C(1N4lco N 000(10 '00 0 'o000 -100W00 0to0 06.be 4000

__ _ _ __ _ _ *0 -. . . . .t

400

m 0. u

w - O- 4I 4N'

X 00 a D00W 00 D O 0 0 V) 0 0 0W)M0 M0M0

on 044' n In 0' 0I~4~0 0 0 0n4

C 00 00 00OD0 0CC00000 r00 G

0 . 4..4 4 -4 .. 4 o44l4 4 4- .4 44- . N.4N4 4 m4. M

0

t-. 0 C4 40 0 4 a 0

C- - .) j

2=1

NO 4 00 4. c0 c'

. 0 0 0 0 N0 0 0. Es - q. 0-- 0 -4 0

40 .~ C4 W) t- m -gm 040 CA 4) N.) N

o Nl 40 .4 04 4 a- C4fl 400 s-c le

N 0NS.o0 in0Sf.0 0 0 N 40fl M0 0f v n 09 mi

0o a - 9 -N- ! It 40 404 0 0 0t 0! 0 l El 40 a! 0

C! r: C! 0! a!' 0' 0. el g!.

.4 -44 - -4 4 4 -4 d-. -4 d -4- - .4

4a a 0 0. E40f.0N 00.0 ID 1 0 1.0 04

OOO NO OON NO N NNO 41l

v. 03000NQC40 C140In

0 00k)00 4n00 0 0 0400 0 00

o0 o aN..

40 0 0 a Sn n 0' 0~ 40 a~ 0 . 0a

04 0n0. 0X 0 0 0 0 0 0 0 0 0 0 0 0 0

0.0

In -n 0 0 0, 0' In In on0 In .4 04 . 'to . ot a4 Nt 00 w 0 m cl 0 0 0 o

to >. C ; 0 "0

cn C4

o ~ ~ ~ s Sn S 0 0 0 0 0 Sn 0 sO s 0

ci C$U

oC0 00 0$ 0 0- 0 04 04 0 0 0 0 0- w m 0 0 m. 0 0- 0

t, 0000 o

00 I-

0 41 0

41C

S. 0 -0 u _______________

- r - -i

ap 00 0 0 0000 0 00

0 00 04 0 00 .0sO f 000.

W.41U#. 0~

* 0 fA* 00 v~0 001 i40a. .. 0 0..to 0 C R- .

ci C; a3 0 a0 a

014 C) @. 0( Is 0 4O O 0 @ @ O

4% C64 o o- - u v . 0 t11 o Q0e y w OVvIV01

-e We 14-t I

j 42

- n 'o 0- In

V) * o n 0 n 11 1 n W)0 t4C

C

11 o 1") 0 ) 04a t- C N 0n

C- C!- C- G!

II O CO O C C 01 c Sn 00 a m0 0 0 S n 00a 0 InOti olC r-N 30CCC~t - ~)0Q 0 0 0)0 C, 00

4-1 0 00 0 00 a 0

. .~ .1.. q.... .5 * .0 . 0 0 0 0 0 0 0 0 0

es I N. 0C0can CC5 N0 In 0 0 a n0S0a n 0 In c inr. i l It) 0)0 ) In Nj.5.SnN - )N In0 If) 010n 4c " -cC

. . . . . . .. .

E-4400

m1 IN 0 0 N 0 .. C. 0 0 0 C4 00( IN wo 0000000000!!000000000!2 -,"!!0 00000a

ol c N00N00CIO00000 Ci ca0

00

V: 0 ~ C1 4NN0a00C'-4 VVV_ V_ VV V____VVV__VVV_ V_ V_

u 010 In 01 a . I 0 Inn no4 n 0 -A a .IM 0 In 0 q0.N. to C- N 0- 0 Sn - CO' n C 00N-I401 C-1 In 0 V 0 A

Er- -144.-- N~ C.00111100 ) -W -4 w 0000-. a 0 0. cl m0 0 m m M m m m v v v v01010

In 000m000 00 0N0 00v00 0Co 0 00000t

c 1' 1 to .1 An n Sn Sn n to Sn Sn Sn Sn Sn WS 0 o0 000 0IN 0

f. N 0 .0C

a . -I, m w 'a 0 r. I* a

43

CC

Q 0 ko

0 C, 0 00 0

0 0 0 0 0

. -1m (4 n ?n 0 000 e ) f . 11 t 0 C? a 0

es In to 30 0 o t o001 0N 0 M0 NN. NS N C. 4040N4 C3 4 N0N 04 4 41 - iiv iiiv NNC.)a)0 4 eq-v C 0 0 t- 400 0000C) )00

0o ~ ~~~ 0000000000 o0000o

v, v. V. V V V ,Ic. r. c'] 14

0 - 0 0

c .. 000 0 m n v V) 0

C 4 M C1 M 4 M C N N M 0 01 M n04C)C

0~~~ 00 I nO O 4 0 N 4 4 .00a-

00 0~. 0C304to 0 w0oCo3 a' 0 00 0 00 4;-00 00 000 W). 000000 (

00

0. .. M4

0 0100 4 0- 04 0 N 4 -q '0 Na C el NN 4 N 4 14 N N m. N- .4

0 I0( ! 0 0. 0 20 .404 0 0 0 . 0 0 0 0 a 0 00

o a 0 0 0 o o 0 0 0 0 - -4 o4 o4 .4 a. o4 a 04 04E*. C; 4 0:4 a4 04 N 04 04 04 N; m, 04 04 04 N* t- V0

- a~ (4 a4 0 0 0 a 0 0 0 0 a 03N 0 0 a 0

M0 -b0 -00000 000000000 o tot.0000o 1. 0 4 I -0 00 No 000cc&to4go0a0go al-a%

0440 000 q. 414 14 4o

144

o ~~ eq 1w m In C- C4 m C) mN. 0)Mcl 0 o100 00 0 0 0

-~I 00 0 00 0

wa toIan 0 V n I)I 1 N m -1 00 c4 0 N ____tot _m 0 0 0 tx a

C-1 N N~ 'lj c.) 1? 1 C

-1 -4 1.0 14 N .o w 4

ta

~. N 4 In 00 W t 01 C j 01 -4 r4 Cl tO aO -1 0 (0 0 .4 0 0 CO 0l 0

a )r )c N In

00.l

E-4 ~ 0 t- 0 t 0 m 0 0 t, vw 0 I 0 v

0 0- 0 0 30 m, , -4NNN01C1 NN01~10(1010N0N ca 040 11111

0000 0000 0000 0000 0000

(0 -VC,

N m0 v0 I- 11) t 0 .4 .I 4 0 q C4 m O V to to N 0. Im 4 3 40 00aa N c - W

C.)I~* Cl 1 4 0 1 M Im N 1 0 1 v 1 f 0 C 0 i 1 01

coc .I V l0 0.0all m 2.0 In 0 01 A m0m CD C N C4 C

IN N N _ )I N *m 0 c

C s1 0 2 0 C q 4C

? . ? .9 9 9 9 1 . . . . CC ?a

v4 t-C 1 0 0 0 a4 m N m N N N a4 C4 v In W .40aaI

- _ __ __ __ ___ __ ___45D

C1 C M-00C C0~. 4 C1 (4OIn04aN 4 M

.0

ta~ca 00, .4 to v__ _ _ _ _

aa a t- 0 .0 o Ie. x. enc i 00 0 4C

N M . 0VNM 0to.0G) w -0 to m *) 0 m 0 0 0 __ ___ __

Ci 0 04 0 0

1, a 0

0o0 0 N C~~S~.N C1 D01aN

0:.3 - 3 i )a 9 0i

-e to 010N 0 00 N 0 0 0 n 1 0cn

en 04mm NNNC4t-O4m4NnI4 of4O4Snm Sn-N eq m C4-~ 0 Cl 0CQ0OCCC)~C 00~. N ) 0

9 1 1 1 .t

00

to 'r go 0 0 in In on on0a0 on0 0 a0 00 t .3 C4 . .0.C -a1 )1

F. lann~U M .v i 90 . 9 . itP-4 r4Ion n~~

Ci4C04~* nSnSnS4S St

C> C0: - r~ 4 .I 0n -C14~ r4 cl U4,4C- 1

'4 C', C4

___ r 4 . -4 4 C,4 e'J (4 C'4 CIAJ -

0 L0 U, 4Ln ~ ~ ~ ~ ~ ~ ~ S coO (" " m r M%

0- CCi 44J (',,4

%0 10 '* 0 r- o' 0 .t 4 r.4 .-4 -c - Si (i (ij (i e' Sto.

CU g: iN (S-I CA Nr

~~~- m.0 ~ 4 -co 0 (N, %0 0 i 0 a

'A 34 14 - 4 C4 N _ _ _ _ _

-4 L rl 0 0N 0 - (i c~.4 W! ON Ch ONt 0%t -cq>

(N (N, 4Si C-4 e-i CI4 i I , '

14co0 %0 -4 , n ul r U,' c,~

q Ln Ln, L A, I .L

00 0 en U) I. o~ U, 0 n C' rJ V

50 0 . 0 , U U, U , ,

-4 -- - - '- ~ ~ _

47

ciJ Ln -4) uj , ) in7-4 -4- )0 C) q]C e

i H C-44 V -4

0I ON I c

It, 00 0

CD a, I 'D D o H

00: 00 m-4C - -

-n %0 r 0-

.4 WU

C' .4 Iwl LI

0 ~ II,.~'...

coi

C 11Ln 61

44 0 0 0

-4-48

00 0

ccr- c

o) II C1 I4 mC

Sri i0 I %OJ C, IC'- IT

ii4 _ _4 -r ___Lf

NJ C-4 -4 C4C4L

en I IL

CD, CD -4 L' 1twr Si Sr r

'51: I 49

ON0 H' '.0 . ' D : _'.o 0 o C14 0 o C4 0

I r. r- i-1 . C1

ol coo' u-c

Z 04 M IT -ON

H- N 0 O N o'-t r - ' 0 -4 - C a'.Oc,4'4 c'r- c,4 m- 00~ oo O N a,

~ ru- u-- .o r-0 '.0 %:'. -

0 C', 000

0. 0 0 (120 0 44c,. i cd I~ r-i t 4 ) H4. 4) t~41 H

m- r- 0r (L 0O 0~ O0C0 ,-4 0 04 0 10 1- H 0

ca QU a)U 3 0 044 o i 44 w0 41 twp t

Cn 0 " 1 0 -1L )1

;> (n >0 . 0 >0n0 >4

~~~~$ +- 0' t . '~0 4.j~4 )r

0 H 10 "aia V10t4U U r- Cjo E 3ri(dd 0 ) -H 00(0 0 C-4 00 r-

0~~ 0i(a

0o 4 0.0 0 0 ca w

co m "0 0 01 - C 0 0 'U 4 0 :j E-2 0 :1 E-4 I)

WU 0) 0

sCd N. sC ~ d4 N~

E-4 w41 001 0 0) 01 00

w 0. 0 0. 0.6 06 06 -

0

936 if. if if io 0 0 0 0 00

" -4 r-q u- r r

ta C41 cO4J41 41 m 44. m 14! c1141- ->__ .(a_ 0 A >w >m >

'p44

-41

ca cc cc cccd w0

APPENDIX III

REFERENCE HEAT-TRANSFER COEFFICIENTS

In presenting heat-transfer coefficient results it is convenient

to use reference coefficients to normalize the data. Equilibrium stag-nation point values derived from the work of Fay and Riddell* were used

to normalize the data obtained in this test. These reference coefficients

are given by:

1/2 0.4 0.25

8.17173(PT2)1(MUTT)0[1 - p ] [0.2235 + (1.35 x 10 )(TT+560)]H(REF) =PT

(RN) /2(TT)0.5

and -

H (REF)STFR =(RHO)(V) [0.2235 + (1.35 x 10-5 )(TT + 560)]

where

PT2 Stagnation pressure downstream of anormal shock wave, psia

MUTT Air viscosity based on TT, lb -sec/ft 2

f

P Free-stream pressure, psia

TT Tunnel stilling chamber temperature, *R

RN Reference nose radius, (0.0175 ft or

0.04 ft determined by model scale)

3RHO Free-stream density, Ibm/.t

V Free-stream velocity, ft/sec

-

Fay, J. A. and Riddell, F. R. "Theory of Stagnation Point Heat Transfer

in Dissociated Air," Journal of the Aeronautical Sciences, Vol. 25, No.2, February 1958.

51

APPENDIX IV

SAM4PLE TABULATED DATA

ii 52

.6.4 ..d~I- 3 333 3 3 0 3 3 . ' . 3.3 mz c) j > 3

C4..

~...Q S

.3 D

.V1-Z) a 4a

.-- ,' 3 3 0c3 C ~ '3 . 3 O 3 3.34.', ~ x o. 2 . 3 3 3 3

o,2. Zm z4 4

D4 Pt 44. z300 c33 ~ 0 3 3 3 3 3 . 3 0 )

540 Z * ~ 42 oooo 03 .3 C 33'3 33 3303 30A

a. .

-3.3

00D

Q6 03 4

o-0 r..~ zm ma.m m m a. a a 4 ca * m aZ ....- 3 -3434 .3.4. P- £C%.~-SC

3.0 1. 4t.~ o 7 r 'a71. L.1 A 3 - At v£ 4 q -r.3aA .4 f c4-. 0 Q~4 14 ' cA o.4 J4

'0 .4o

f.0 C 3r

* 0

44 S. nA 4 r

%2C , S C - 14 % j '4 1 Zcft4 ) ' uN 4. tl4

14. o" . . .l .4 t1 11 1

a. I a..3.1 !:- 'a'44) .41744 4-43i1. '*.. 44"-

-. 94

-& -t 2..1 ar qe4' r A u. ,A A 4At4 )J 4#? S.0

mb. 41 m0 1- mamm In ms , lm a mac mamm

OI4:1%4DO w 31.

0 442 1% 421

A ~.43 353