WIND-TUNNEL INVESTIGATION

(1)

LOAN

COPY:

RETURN

TC)

KIRTLAND AFB,

N

MEX AFWL (WLdi-2)

WIND-TUNNEL INVESTIGATION

OF THE AERODYNAMIC

PRESSURES

O N THE APOLLO COMMAND

MODULE CONFIGURATION

by IVillium C.

Moseley, Jr.,

und

B. J . Wells

M u n n e d Spucecruft Center

Houston,

T e x a s

N A T I O N A L A E R O N A U T I C S A N D S P A C E A D M I N I S T R A T I O N W A S H I N G T O N , D . C. OCTOBER 1 9 6 9

(2)

TECH LIBRARY KAFB, NM

. R E P O R T NO.

12.

G O V E R N M E N T A C C E S S I O N NO.

NASA TN

D-5514

I

.

T I T L E AND S U B T I T L E

WIND-TUNNEL INVESTIGATION OF THE AERODYNAMIC PRESSURES ON THE APOLLO COMMAND MODULE CONFIGURATION

'. AUTHOR (S)

William C. Moseley, J r . , MSC, and B. J. Wells, ITT, Federal Electric Corp.

I. PERFORMING ORGANIZATION NAME AND ADDRESS

Manned Spacecraft Center Houston, Texas 77058 2. S P O N S O R I N G A G E N C Y N A M E A N D A D D R E S S

National Aeronautics and Space Administration Washington, D. C. 20546 5 . S U P P L E M E N T A R Y N O T E S 16. A B S T R A C T 122 5 . R E P O R T D A T E October

1969

6 . P E R F O R M I N G O R G A N I Z A T I O N C O D E 8. P E R F O R M I N G O R G A N I Z A T I O N R E P O R T NO. S-219 IO. W O R K U N I T NO. 914-50-10-03-72 I I . C O N T R A C T OR G R A N T NO. 13. R E P O R T T Y P E A N D P E R I O D C O V E R E D Technical Memorandum 14. S P O N S O R I N G A G E N C Y C O D E

A program of wind-tunnel tests was conducted at Mach numbers from 0 . 4 to 19. 0 to determine the pressure distribution of the Apollo command module. Data are presented for the angle-of- attack range from 0" to 180". Results of these tests are presented as pressure coefficients plotted against the physical positions of the orifices.

17. K E Y W O R D S ( S U P P L I E D B Y AUTHOR)

.

Aerodynamic Characteristics * Apollo

' Command Module * P r e s s u r e Coefficient

Wind Tunnel ' Scale Model

Manned Spacecraft 18. D I S T R I B U T I O N S T A T E M E N T IS. S E C U R I T Y C L A S S I F I C A T I O N h H I S R E P O R T ) 20. S E C U R I T Y C L A S S I F I C A T I O N 21. NO. O F P A G E S 22. P R I C E S HIS PAGE) Unclassified Unclassified ₇₇ $3.00

(3)

(4)

I II

CONTENTS Section Page SUMMARY

. . .

1 INTRODUCTION

. . .

1 SYMBOLS

. . .

2

MODELS AND TEST TECHNIQUES

. . .

3

FACILITIES

. . .

3

TEST CONDITIONS AND ACCURACY

. . .

4

T e s t Conditions

. . .

4

Accuracy

. . .

4

SUMMARY OF RESULTS

. . .

4

REFERENCES

. . .

5

(5)

TABLES

Table Page

I TEST FACILITIES

. . .

6 I1 TEST CONDITIONS

. . .

7 III ESTIMATED ERRORS

. . .

8

(6)

FIGURES

Figure Page

1 Body-axis s y s t e m .

. .

. . .

. .

.

. .

.

. . . .

.

. .

. . .

. .

9

2 Sketch of Apollo command module. Dimensions are given in full-scale inches; however, drawings are not to scale

(a) Command module configuration C1

.

. . .

. .

.

10 (b) Command module configuration C2

. . .

.

. . .

.

. .

11 (c) Command module configuration with s t r a k e s

(configuration C38L28)

.

. . .

.

. . .

..

.

. . . .

. .

12 3 Photographs of test models

(a) AEDC-C, heat shield forward, configuration C 2

.

. . .

1 3 (b) Ames 2x2 TWT, configuration C1

.

. .

. . . . .

. . .

1 4 4 Pressure-orifice locations

(a) 0.02-scale pressure model, configuration C1. Apex forward: positive s in positive Z-direction. Heat

shield forward: positive s in negative Z-direction

. . .

.

1 5 (b) 0.04-scale pressure model, configuration C2. Posi-

(c) 0.045-scale pressure model, configuration C Apex

tive s in negative Z-direction

. .

.

. . .

.

. . . . .

.

. .

.

16 2'

forward: positive s in positive Z-direction. Heat

shield forward: positive s in negative Z-direction

.

17 (d) 0.05-scale pressure model, configuration C Posi-

2 '

tive s in negative Z-direction

.

. . . .

.

. .

.

. .

. . . .

.

18 5 Variation of C with increasing ct at X = O D , X = 45",

P

and X = 90" at M = 0.4, 0.02-scale model, configuration C1, apex forward, in the Ames 2x2 TWT test facility

(a) ct

= O "

to ct = 6 1 "

. . .

.

. . .

.

. . .

.

19 (b) ct = 79" to ~r = 140"

. . .

20

(7)

Figure

6 Variation of C with increasing cy

at

X = 0", h = 45", P

and X = 90"

at

M = 0.7, 0.02-scale model, configuration C1, apex forward, in the Ames 2x2 TWT

test

facility

(a) cy = 0" to cy = 6 1 " .

. . .

21 (b) = 79" t o cy = 140'

. . .

22

7

Variation of C with increasing cy

at

X = 0", X = 45",

P

and X = 90"

at

M = 0.9, 0.02-scale model, configuration C1, apex forward, in the Ames 2x2 TWT

test

facility

(a)

cy = 0 " t o cy = 6 1 " .

. . .

23 (b) CY = 79" to CY = 140"

. . .

24 8 Variation of C with increasing cy

at

X = 0", X = 45",

P

and X = 90"

at

M = 1.1, 0.02-scale model, configuration

C1, apex forward, in the Ames 2x2 TWT

test

facility

(a) cy = O o to cy = 6 1 " .

. . .

25 (b) cy = 79" to Q = 1 4 0 "

. . .

26

at

X = 0", X = 45", P

and X = 90"

at

M = 1.2, 0.02-scale model, configuration C

,

apex forward, in the Ames 2x2 TWT

test

facility

1

(a)

cy = 0" to cy = 6 1 " .

. . .

27 (b) (Y = 79" to Q = 140"

. . .

28

at

X = 0", X = 45

",

P

and X = 90"

at

M = 1.34, 0.02-scale model, configuration C1, apex forward, in the Ames 2x2 TWT test facility

(a)

cy

= O "

to cy = 6 1 " .

. . .

29

(b) cz = 7 9 " t o CY = 140"

. . .

at

X = 0", X = 45",

P

and X = 90"

at

C1, apex forward, in the JPL-20SWT test facility

(a)

cy = 0" to (Y = 6 0 " .

. . .

31

(b) cy = 80" to cy = 140"

. . .

32

(8)

Figure

12 Variation of

c

with increasing cy at X = 0",

X

= 45", and X = 90"

at

M = 2.01, 0.02-scale model, configuration C1, apex forward, in the JPL-BOSWT test facility

P

(a)

cy = 0" to cy = 6 0 " .

. . .

33 (b) cy = 80" to (Y = 140"

. . .

34

at

X =

O",

X = 45", and X = 90"

at

M = 3.01, 0.02-scale model, configuration C1, apex forward, in the JPL-20SWT test facility

P

(a)

cy = 0" to cy = 6 0 " .

. . .

35 (b) cy = 80" to cy = 140"

. . .

36

14 Variation of C with increasing cr

at

X = 0", X = 45", and X = 90" at M = 3.99, 0.02-scale model, configuration C1, apex forward, in the JPL-20SWT test facility

P

(a)

CY = 0" to cy = 60"

. . .

37 (b) cy = 80" to CY = 140"

. . .

38 15 Variation of C with increasing cr at h =

O",

X = 45",

and h = 90" at M = 5.01, 0.02-scale model, configuration C1, apex forward, in the JPL-20SWT test facility

P

(a) cr = 0" to cy = 6 0 " .

. . .

39 (b) cy = 80" to cr = 140"

. . .

40 16 Variation of C with increasing cr

at

X = 0", h = 45",

P

and h = 90"

at

M = 7.35, 0.02-scale model, configuration C1, apex forward, in the JPL-21HWT test facility

(a) ct = 0 " t o cy = 6 0 " .

. . .

41 (b) cy = 80" to CY = 140"

. . .

42 17 Variation of C with increasing cy at h = 0", X = 45",

P

and X = 90"

at

M = 9.08, 0.02-scale model, configuration C1, apex forward, in the JPL-21HWT test facility

L

(a) cy = 0" to cy = 6 0 " .

. . .

43 (b) cy = 80" to cy = 140"

. . .

44

(9)

Figure Page 18 Variation of C with increasing cy

at

h = 0", h = 45",

P

and X = go", 0.045-scale model, apex forward, in the AEDC-C

test

facility

(a)

cy = 0" to cy = 60"

at

M = 1 0 . 1 , C 2 .

. . .

45 (b) cy = 80" to a = 140"

at

M = 10.0, C38L28

. . .

46 19 Variation of

c

with increasing cy

at

X = 0", X = 45",

P

and h = 90"

at

M = 0.4, 0.02-scale model, configuration C1, heat shield forward, in the Ames 2x2

TWT

test facility

. . .

47 20 Variation of

c

with increasing cy

at

X =

o",

h = 45",

and X = 90"

at

M = 0.7, 0.02-scale model, configuration C1

,

heat shield forward, in the Ames 2x2

TWT

P

test facility

. . .

48 21 Variation of

c

with increasing cy

at

h =

O",

X = 45",

P

and h = 90"

at

TWT

test

facility

. . .

49

at

h = 0", h = 45", and h = 90"

at

TWT

P

test facility

. . .

50 23 Variation of C with increasing a

at

h = 0", X = 45",

P

and h = 90"

at

M = 1 . 2 , 0.02-scale model, configuration C1, heat shield forward, in the Ames 2x2

TWT

test facility

. . .

51 24 Variation of C with increasing a

at

h = 0", h = 45",

P

and X = 90"

at

M = 1.34, 0.02-scale model, configura-

tion C1

,

TWT

test

facility

. . .

52

(10)

Figure

25 Variation of C with increasing a,

at

X =

o",

X = 45O, and X = 90"

at

M = 1.48, 0.02-scale model, configuration

C1,

heat shield forward, in the JPL-2OSWT

test

f a c i l i t y .

. . .

53 P

Variation of C with increasing a,

at

X = 0", X = 45", and X = 90"

at

C1

,

heat shield forward, in the JPL-2OSWT test

f a c i l i t y .

. . .

54 P

Variation of

c

with increasing a,

at

X =

O",

X = 450, P

and X = 90"

at

M = 3.01, 0.02-scale model, configuration

C1,

heat shield forward, in the JPL-2OSWT t e s t

facility

. . .

55 Variation of C with increasing a,

at

X = 0"

,

X = 45

",

P

and X = 90"

at

M = 3.99, 0.02-scale model, configuration C1, heat shield forward, in the JPL-2OSWT t e s t

facility

. . .

56 Variation of C with increasing (Y at X =

O",

X = 45

",

and X = 90"

at

M = 5.01, 0.02-scale model, configuration C1, heat shield forward, in the JPL-20SWT test

facility

. . .

57 P 26 27 28 29 30 31 32

Variation of C with increasing a, at X = O", X = 45", P

and X = 90" at M = 6.07, 0.02-scale model, configuration

C1,

heat shield forward, in the JPL-21WT test

facility

. . .

58 Variation of C with increasing a, at X = 0", X = 45",

and X = 90" at M = 7.35, 0.02-scale model, configuration

C1,

heat shield forward, in the JPL-21HWT test

facility

. . .

59 P

Variation of

c

with increasing a, at X =

O",

X = 45", and X = 90"

at

C1,

heat shield forward, in the JPL-21HWT test

(11)

Figure Page 33 Variation of C with increasing cy

at

X =

O",

X = 45",

P

and X = 90"

at

tion C2, heat shield forward, in the AEDC-C

test

facility

. .

at

X = 0", X = 45",

P

and h = 90"

at

tion C2, heat shield forward, in the CAL-48HST

test

facility

. . . .

at X

=

O",

X = 45",

P

and X = 90"

at

tion C2, heat shield forward, in the CAE-48HST test facility

. . . .

63 36 Variation of C with increasing CY

at

X = 0", X = 45",

P

and X = 90"

at

test

facility

.

64 37 Variation of

c

with increasing

a at

X =

o",

X = 45",

P

and X = 90"

at

test

facility

. . .

at

X = 0", X = 45",

P

and X = 90"

at

test

facility

. .

.

66 39 Variation of C with increasing CY

at

X = 0", X = 45",

P

and X = 90"

at

tion C2, heat shield forward, in the AEDC-HS

II

test facility

. . .

.

67

(12)

WIND-TUNNEL INVESTIGATION OF THE AERODYNAMIC PRESSURES

ON THE APOLLO COMMAND MODULE CONFIGURATION

By W i l l i a m C. Moseley,

Jr.,

a n d B.

J. Wells*

Manned Spacecraft Center

SUMMARY

Wind-tunnel tests were conducted

at

several facilities to determine the pressure distribution over the Apollo command module

at

Mach numbers from low subsonic speed to hypersonic speed. The Mach-number range is 0.4 to 19.0, and the angle of attack varies from 0" to 180".

The data obtained from these tests are presented in this paper as p r e s s u r e coefficients plotted against the physical positions of the orifices. Only limited data are presented in the angle-of-attack range from 0" to 140"; the a r e a of concentration is the angle-of-attack range from 150" to 180" because this is the trim-angle-of-attack range for atmospheric entry.

I NTROD UCT

I ON

In late 1959, personnel from several NASA Centers recommended a circumlunar flight and an earth-orbiting laboratory program to be called the Apollo Program. This program w a s initiated and w a s assigned to the NASA space task group.

On

May 25,

1961, the Apollo Program w a s reoriented toward achieving

a

manned lunar landing as part of the continuing program of space exploration following Project Mercury and the Gemini Program.

To satisfy the design criteria and guidelines for an Apollo spacecraft, many pos- sible configurations were considered. The basic configuration chosen for development w a s the one determined to be most practical with respect to the current development of the state of the

art.

Once the configuration w a s determined,

it

w a s necessary to evaluate the basic design of the Apollo spacecraft thoroughly. One means of evaluating the basic design w a s the Apollo wind-tunnel testing program (AWTTP). This program is discussed in detail in reference 1. Early wind-tunnel studies that were used to support and verify the basic design

as

the most practical are discussed in references 2 to 5.

*ITT/Federal Electric Corporation. -

(13)

Investigations

were

made

as a

p a r t of the AWTTP to determine the aerodynamic loads on the Apollo command-module (CM) configuration. Pressure distributions were determined

at

Mach numbers from 0.4 to 19.0 over

an

angle-of-attack range of 0" to

180". Data are presented in this paper

as

pressure coefficients plotted against the physical positions of the orifices.

SYMBOLS

The positive directions of the body-axis system,

as

referred to in the following list, are shown in figure 1.

cP pressure coefficient, (pX - Pm)/qm

D maximum diameter of CM

(154

inches full scale)

M Mach number

pX o r i f i c e p r e s s u r e

Po0 f r e e - s t r e a m s t a t i c p r e s s u r e

qm f r e e - s t r e a m dynamic pressure, 1/2pV2

R radius

Re Reynolds number (based on maximum model diameter)

r radius of C M

at

maximum diameter

S distance to orifice from the center of the apex o r of the heat shield of the model, measured

along

the surface, positive in the positive Z-direction f o r apex-forward mounting and positive in the negative Z-direction for heat- shield-forward mounting

V velocity

X, Y, Z body reference axes

cy angle of attack in the XZ-plane

h angle of instrumentation plane relative to pitch plane

P

air

density

(14)

MODELS AND TEST TECHNIQUES

The CM body-axis system is shown in figure 1, and sketches of

test

models with controlling dimensions are shown in figure 2. Typical photographs of test models mounted in

test

facilities

are

shown in figure 3.

The models tested vary in scale f r o m 0.02 to 0.05; the configurations are shown in figure 2.

Data were determined for. attitudes with both apex (small end) and heat shield (blunt face) forward. The apex-forwardattitude was designatedas a = 0'; and, through the use of a series of modules,

data

were determined at designated angles of attack from 0' to 180'. All the modules were sting-supported, and the sting attachment

was

usually in the

wake

of the model. The ratio of sting diameter to model diameter varied from facility to facility, and no attempt has been made to correct the data for sting- interference effects.

Static pressure orifices are located on the surface of the Apollo CM. The physical position of an individual orifice is indicated by the ratio of s/r,

as

presented in figure 4, for the models tested.

Each orifice was connected to

a

calibrated pressure transducer, and the result- ing pressure readings were reduced to the standard pressure-coefficient form by using the following equation:

FACILITIES

The broad range of expected flight conditions (M, Re, and a ) and the limitations of

a

wind tunnel to simulate all these conditions dictated the use of certain test facilities. The facilities used to acquire pressure distribution on the CM configuration are listed in table I, along with wind-tunnel s i z e s and capabilities. These facilities in- cluded the Arnold Engineering Development Center Tunnel C (AEDC-C), the Ames 2- by 2-foot transonic wind tunnel (Ames 2x2 TWT), the Jet Propulsion Laboratory

20-inch supersonic wind tunnel (JPL-2OSWT) and 21-inch hypersonic wind tunnel (JPL-BlHWT), the Arnold Engineering Development Center Hot-Shot 11 impulse tunnel (AEDC-HS 11), and the Cornel1 Aeronautical Laboratory 48-inch hypersonic shock tunnel (CAL-48HST).

3

(15)

TEST CONDITIONS AND ACCURACY

Test Conditions

Test conditions are listed in table I1 according to the facility used.

Accu

racy

Table 111 is

a

list of estimated errors encountered in the

test

facilities utilized in this study.

SUMMARY

OF

RESULTS

Static and dynamic characteristics of the Apollo CM (with and without surface protuberances) were investigated and are presented in reference 6; the effects of vary- ing certain geometric dimensions of the basic CM configuration are presented in reference 7. The pressure-coefficient data for these configurations are presented herein with a minimum of analysis.

The data presented in figures 5 to 39 a r e plotted as pressure coefficient versus physical position of the orifices, with the pressure coefficient having three data planes:

h = 0

',

h = 45

',

and X = 90

'.

(Values of X and s/r for various model orifice num-

bers are presented in figure 4. ) The results of this report are summarized in the following figures.

1. Figures 5 to 18 present the variation of the pressure coefficient with increasing angle of attack from 0

'

to 140

'

at Mach numbers from 0.4 to 10. 1 in the apex- forward attitude.

2. Figures 19 to 39 present the variation of the pressure coefficient with increas- ing angle of attack from 140

'

to 180 at Mach numbers from 0.4 to 19.0 in the heat- shield-f orward attitude.

Additional information and data are available in references 8 and 9.

Manned Spacecraft Center

National Aeronautics and Space Administration Houston, Texas, August 4, 1969

914-50-10-03-72

(16)

REFERENCES

1. Moseley, William C.

,

Jr. ; and Martino, Joseph C. : Apollo Wind Tunnel Testing P r o g r a m - Historical Development of General Configurations. NASA TN D-3748, 1966.

2. Morgan, J a m e s R. ; and Fournier, Roger H. : Static Longitudinal Characteristics of

a

0.07-Scale Model of

a

Proposed Apollo Spacecraft

at

Mach Numbers of

1.57 to 4.65 (C). NASA TM X-603, 1961.

3. Pearson, Albin 0. : Wind-Tunnel Investigation of the Static Longitudinal Aerody- namic Characteristics of Models of Reentry and Atmospheric-Abort Configura- tions of

a

Proposed Apollo Spacecraft at Mach Numbers from 0.30 to 1.20 (C). NASA TM X-604, 1961.

4. Pearson, Albin 0. : Wind-Tunnel Investigation of the Static Longitudinal Aerody- namic Characteristics of

a

Modified Model of

a

Proposed Apollo Atmospheric- Abort Configuration

at

Mach Numbers from 0.30 to 1.20. NASA TM X-686,

1962.

5. Fournier, Roger H . ; and Corlett, William A. : Aerodynamic Characteristics in Pitch of Several Models of the Apollo Abort System from Mach 1. 57 to 2. 16. NASA TM X-9

IO,

1964.

6. Mosely, William C.

,

Jr. ; Moore, Robert H.

,

Jr. ; and Hughes, Jack E. : Stability Characteristics of the Apollo Command Module. NASA TN D-3890, 1967.

7. Moseley, William C . Jr. ; Graham, Ralph E . ; and Hughes, Jack E. : Aerody- namic Stability Characteristics of the Apollo Command Module.

NASA TN D-4688, 1968.

8. Deitering, J. S. ; and Brillhart, R. E.

,

Jr. : P r e s s u r e T e s t s on Apollo Configura- tions at Mach Numbers 1 . 5 , 2, 3, and IO ( C ) . AEDC-TDR-63-164, 1963.

9. Knox, E. C. : Pressure Distributions and Force Coefficients Measured on the Apollo Command Module Reentry Codiguration at Mach 19 (C).

AEDC-TDR-62-193, 1962.

(17)

TABLE I.

-

TEST FACILITIES

~~

Facility _testSize _sectionof Mach-number

(18)

(19)

(20)

+Z

Figure 1 . - Body-axis system.

+X

9

(21)

54.0

-

Y

(a) Command module configuration C1.

Figure 2.

-

Sketch of Apollo command module. Dimensions are given in full-scale inches; however, drawings are not to scale.

(22)

Command module configuration Figure 2. - Continued.

C 2'.

(23)

(c) Command module configuration with s t r a k e s (configuration C38L28).

Figure 2. - Concluded.

12

(24)

~

CJ.:)

(a) AEDC-C, heat shield forward, configuration C

2.

Figure 3. - Photographs of test models.

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

_---" ,.. ..

"

~

(25)

14

(b) Ames 2x2 TWT, configuration C 1·

Figure 3. - Concluded.

(26)

Model orifice no. 99 X =

oo

16 h = O O 14

A=oo

1 3

X=oo

12

x =

oo

11

x = o o

1 0 A Z O 0 9

A=oo

8 A = 0' 7 x = o o 6 x = O o 5

A=o0

4 A = O o 3 A Z O 0 2

x = o o

1 x = o o 82

x =

00 8 3 A Z O 0 84

x =

Oo 85 A = '0 86 A = 0' 87 A =

oo

88 A =

oo

89 A = 00 90 A = 00 9 1 A = Oo 92 A = 0 0 15

x =

0' 9 3 A = 0'

1

+Z Y 99 A 9Oo++Y S Apex forward 0.000 - .253

-

.47 0 -.686 -.902

-

1.118 -1.334 -1.550 -1.765 -1.914 -2.052 -2.118 -2.322 -2.455 -2.586 -2.716 2.846 2.716 2.586 2.455 2.322 2.188 2.052 1.914 1.765 1.550 1.334 1.118 .902 Heat shield forward 2.846 2.593 2.376 2.160 1.944 1.728 1.512 1.296 1.081 .932 .794 .658 .524 .391 .260 .130

.ooo

-.130 -.260 -.391 -.524 -.658 -.794 -.932 -1.081

-

1.296

-

1.512

-

1.728

-

1.944

t

+Z

Model orifice no.

94 A =

oo

95 A = 0' 96 A = 0' 99 A = 45' 35 )(= 450 32

x =

45' 30

x =

45' 29

x =

45O 27 A = 45' 25 A = 45' 2 3 X = 45' 1

x =

450 63 X = 45''' 65

x =

45' 67

x =

45' 69

x =

45' 7 0 x=45O 72

x =

45' 75

x =

45O 99

x =

90' 55

x =

90' 52 x=9Oo 50

x =

90' 49

x =

90' 47

x =

90' 45

x =

90' 4 3

x =

90" 1

x =

90° forward Apex .686 .47 0 .253

.ooo

-

.470

-

1.118

-

1.550

-

1.765 -2.052 -2.322 -2.586 2.846 2.586 2.322 2.052 1.765 1.550 1.118 .47 0

.ooo

.470 1.118 1.550 1.765 2.052 2.322 2.586 2.846 H at s ield Forwkd -2.160 -2.376 -2.593 2.846 2.376 1.728 1.296 1.081 .794 .524 .260

.ooo

-.260 -.524 -.794

-

1.081

-

1.296

-

1.728 - 2.376 2.846 2.376 1.728 1.296 1.081 .794 .524 .260

.ooo

(a) 0.02-scale pressure model, configuration

C1.

Apex forward: positive s in positive Z-direction. Heat shield forward:

positive s in negative Z-direction.

Figure 4.

-

Pressure-orifice locations.

(27)

x =

0"

z

3 4 5 6 7 8 9 1 0 11 1 2 1 3 92 9 1 9 0 8 0 88 87 86 6 Model orifice no.

x =

0"

-

x =

0"

x =

oo

x =

0"

x =

0"

x =

0"

x =

0"

x =

0"

x =

0" A = 00

x =

0"

x =

0"

x =

oo

x =

0" A = 0" A =

0"

x =

oo

x =

0"

x =

0"

f

+Z

s/r

Heat shield forward

2.566- 2.179 1.791 1.404 1.084 .984 .897 .712 .530 .352 .175

.ooo

-.175 -.352

-

.530 -.712

-

.897

-

.984 -1.084

'I

t

+Z Model orifice 23 25 26 27 29 3 1 1 3 7 1 69 7 66 45 46 47 49 5 1 1 3 .29 no.

x =

45"

x

= 45"

x =

45"

x =

45"

x

= 45O

x =

45O A = 45"

x

= 4.5O

x =

45"

x =

450 A = 45" A = 900

x =

90"

x =

90"

x =

90"

x =

90'

x =

90"

x =

90' s/r

Heat shield forward

2.175 1.404 1.084 .984 .712 ,352

.ooo

-

.352 -.712 -.984 -I ,084 1.404 1.084 .984 .712 .352

.ooo

-.712

(b) 0.04-scale p r e s s u r e model, configuration C2. Positive s in negative Z-direction.

Figure 4. - Continued.

(28)

Model orifice no. 1159 A = ( ? 1 1 9 i = O 0 1069 k = O0

t

+Z 5 Apex f a w a r d 0.000 -.Ob4 -.118 -.208 -.289 -.497 -.936 -1.155 -1.372 -1.589 -1.742 -1.797 -1 3 5 4 -1.918 -1.979 -2.034 -2.354 -2.085 -2.626 2 3 8 6 2.626 2.354 2.143 2.085 2.034 1.918 1.979 1 .E54 1.797 1.742 1.589 1.372 1.155 .936 .497 ,289 .208 .118 .Ob4 -.ooo -.208 -.118 -.289

=I1

leat shield 2.886 2.822 2.768 2.678 2.597 2.389 1.950 1.731 1.514 1.194 1.297 1.089 1.032 .968 .907 .852 .801 .532 .260 .ooo - .260 - .532 - .743 - .801 - .852 - .907 - 1.032 - .968 - 1.089 - 1.297 - 1.144

-

1.514 - 1.731 - 1 . 9 5 0

-

2.389 - 2.678 - 2.597 - 2.768 - 2.822 2 3 8 6 2.762 2.672 2.597 Model orifice no. forward Apex -.497 -1.046 -1.155 -1.372 -1.589 -1.742 -1 .E54 -1.797 -1.918 -2.085 -2.354 2.886 2.354 2.085 1.918 1.854 1.797 1.742 1.589 1.372 1.155 .936 .497 .289 .208 .118 .ooo .Ob4 .118 .2 08 .289 .497 .936 1.155 1.372 1.589 1.742 1.797 1.918 1.854 2.354 2.085 2.886 leat shield forward 2.389 1.950 1.7'31 1.514 1.297 1.144 1.089 1.032 .968 .801 .532 .ooo - .532 - .801 -1.032 - .968 -1.089 -1.144 -1.297 -1.514 -1.731 -1.950 -2.389 -2.597 -2.672 -2.762 2 .E86 2.822 2.762 2.672 2.597 2.389 1.950 1.731 1.514 1.297 1.144 1.089 1.032 .968 3 0 1 .532 .ooo

(c) 0.045-scale pressure model, configuration C2. Apex forward: positive s in positive Z-direction. Heat shield forward: positive s in negative Z-direction.

Figure 4. - Continued.

(29)

Model orifice no.

x =

0" 7 2 +Z +Z 2 1 20 19 1 8 7 6 5 4 3 2 1 1 5 1 6 1 7 2 1 23 2 2 1 0 9 8 1 1 3 1 4 2 1 26 24 1 2 11

1 x =

0" A = 0"

x =

0"

x =

0"

x =

0"

x =

oo

x =

0"

x =

0" h = 0"

x =

0"

x =

0"

x =

0"

x =

0"

x =

0"

x =

45

x =

45" A = 45" I = 45"

x =

45" A = 45"

x =

45"

x =

45"

x =

90"

x =

90"

x =

90'

x =

90' h = 90"

x =

90"

x =

450,

(d) 0.05-scale pressure model, configuration C Positive s in 2'

negative Z-direction.

s/r

(30)

A-45' 0 A m m o 0

-.

5 -L 0 -L 5 -2 0 -3.0 -25 - 2 0 -L5 -LO -.5 0 .5 LO L5 slr

Figure 5.

-

Variation of Cn with increasing a at X =

O",

20 25 3.0

h = 45", and h = 90"

at

M = 0.4, 0.02-scale model, configuration C1, apex forward, in the Ames 2x2 TWT test facility.

I

(31)

(32)

0 A - 0 c P A . 4 5 O A . 9oo L5 LO .5 0 0 0

-.

5 -1.0 -3.0 ! : -25 -20 -L5 -LO

-.

5

(a)

cr = 0'

t

7- I ' t o (Y = 61". Figure 6.

-

Variation of cP with increasing cr LO L5 2 0 at X = Oo, X = 45", and

X = 90" at M = 0.7, 0.02-scale model, configuration C apex forward, in the Ames 2x2 TWT test facility.

1'

(33)

(34)

L5 LO .5 x.oo 0 cP h

-

45O 0 0 X"% 0

-.

5 -L 0 -2.0 -1.5 -L 0 1.0 2 0

t

j

l

(a) CY = O O to CY = 61".

Figure 7.

-

Variation of C with increasing CY at X = 0", X = 45O, and X = 90" at M = 0.9, 0.02-scale model, configuration P C1, apex for-

2 5 3.0

ward, in the Ames 2x2 TWT test facility.

(35)

(36)

1.5 LO .5 0 h - 0 0 I

i

I

!

I

1 /

I

1

I

i

I ! I I ! h-45O 0 : ! 1 : h-90' 0

-.

5 -1.0 ! ' . . ' I ' 0 .5 LO slr L 5 -LO

-.

5 -2 5 -3.0 -2 0 (a) ct = 0" t o cx = 61".

Figure 8.

-

Variation o r C with increasing (Y at X = O o , X = 45", and

X = 90' at M = 1.1, 0.02-scale model, configuration C1, apex forward, in the Ames 2x2 TWT test facility.

P

(37)

(38)

1 5 LO . 5 h - O 0 0 CP h-45' 0 h = W O 0

-.

5 . . . . , I i : : (a) cy = 0" to cy = 61

'.

Figure 9.

-

Variation of C with increasing cy at X = 0": X = 45", and X = 90" at M = 1 . 2 , 0. 02-scale model, configuration C1, apex forward, in the Ames 2x2 TWT test facility.

P

(39)

(40)

1.5 L O .5 h - O 0 0 - a ' 0 0 - 0 20 : O 41 A 61 r I I I , cP h-45O 0 A - 90' 0 7" I . . . I , /I , ' -3.0 -2.5 -2.0 - L 5 -1.0 -.5 0 slr . 5 1.0 1.5 2 0 2.5 3.0 = 61". (a) cr = 0" t o cr

Figure 10. - Variation of C with increasing cr

at

X = 0", X = 45", and

X = 90" at M = 1. 34, 0.02-scale model, configuration C1, apex f o r -

ward, in the Ames 2x2 TWT test facility. P

(41)

(42)

0 h . 0 cp h

-

4 5 O A.mO 0 0

-.

5

I

-3.0 -25 - 1 -L5 -LO -.5 0 . 5 LO L 5 2 5 2 0 slr 3.0

Figure 11. - Variation of C with increasing cr at X = 0", X = 45", and X = 90" at M = 1.48, 0.02-scale model, configuration C apex f o r - ward, in the JPL-2OSWT test facility.

P

1'

(43)

(44)

LO L 5 LO .5 0 1 a 0 0 - 0 20 : 0 40 - A 6 0 A - O 0 A

-

45' A - 5Qo

-.

5 -3.0 -2.5 -20 - L 5 -LO -.5 0 .5 1.0 L 5 str 20 2 5 3.0

Figure 1 2 . - Variation of C with increasing Q at X = 0", X = 45", and X = 90"

at

M = 2.01, 0.02-scale model, configuration C1, apex forward, in the JPL-2OSWT test facility.

P

(45)

(46)

2 0 L 5 LO .5 h.O0 0 T F a cP h

-

45O 0 A m m o 0 -2 0 -L 5 -L 0 0 slr LO L 5 2 0 2.5 3.0

-.

5

Figure 13.

-

Variation of C with increasing cz

at

X = 0", X = 45"' and X = 90" at M = 3.01, 0.02-scale model, configuration C apex for- ward, in the JPL-20SWT test facility.

P

1'

(47)

(48)

2 0 L5 LO .5 h-0' 0 I I I ! I I ' I ! cP

..-

h - 4 5 O 0 h - W 0 0 I * . - I

-.

5 0 .5 1.0 1.5 2.0 2.5 3.0 slr -1.5 = 0' to CY = 60". Figure 14.

-

Variation of C P

X = 90" at M = 3 . 9 9 , 0.02-s~:ale model, configuration

cl,

apex for- rrith increasing

a

at X =

o",

X = 45", and

ward, in the JPL-2OSWT test facility.

(49)

(50)

A

-

0' cP A

-

4 5 O -2.5 Figure 15.

-

-1.5 LO

-.

5 .5 1.0 1.5

Variation of with increasing ct

2.0 2.5

i o 20

' 0 40 I

at X = O", X = 45", and

3.0

X = 90" at M = 5.01, 0.02-scale model, canfiguration C apex for-

ward, in the JPL-20SWT test facility.

1'

(51)

(52)

2 0 1.5 LO .5 0 0 0 m A

-

oo CP A

-

45O h - W O

1

!

i

I I I I

I i ,

I

I!

! I ; ' ! ii i i ! I . , . , .

.

, . slr

(a)

cy = 0" to cy = 60".

Figure 16.

-

Variation of C with increasing cy

at

X = 0", X = 45", and

X = 90" at M = 7.35, 0.02-scale model, configuration C1, apex for- ward, in the JPL-21HWT test facility.

P

(53)

(54)

2 0 L5 LO .5 0 a 0 0 0 20 0 40 I I _{I I} A - O D c P A

-

45O A - 9Oo I 1 0 I ! ! I 0

-.

5 -3.0 -2.5 -2.0 -1.5 -1.0 -.5 0 .5 1.0 1.5 20 2 5 3.0 slr (a) cy = 0" to a = 60".

Figure 17.

-

Variation of C with increasing cy at X = 0", X = 45", and h = 90" at M = 9.08, 0.02-scale model, configuration C1, apex forward, in the JPL-21HWT test facility.

P

(55)

(56)

2 0 L5 LO .5 0 h.0 0

i

I !

cP

: I

. . , . . . - .- h = 45O h . 9 o o 125 - 2 0 -L5 -1.0

-.

5 0 .5 1.0 1.5 2.0 25 3.0 slr

(a)

CY = 0' t o CY = 60' at M = 10.1, C2.

Figure 18.

-

Variation of C with increasing (Y

at

X = 0", X = 45", and

X = go", 0.045-scale model, apex forward, in the P AEDC-C test facility.

(57)

(58)

IIi

1

I

0 a 0 140 0 150 0 160 A 170 b 179 I T 1 1

I

-1.0 1 ' -3.0 t -2.5 -2.0 -1. 5 -1.0

-.

5 _1.0 1.5 2.5 3.0 slr

Figure 19.

-

Variation of with increasing cy _at

x

=

o",

h = 45", and X = 90" at

M

= 0 . 4 , 0.02-scaJe model, configuration C1, heat shield forward, in the Ames 2x2 TWT test facility.

(59)

L 5 1.0 .5 h = O 0 0 A -45" 0 a 140 150 160 179 CP : I : : I L 5 2.0 -1.0

-.

5 0 slr

Figure 20.

-

Variation of C with increasing cy at X = 0", h = 45", and h = 90"

at

M = 0. 7, 0. 02-scale model, configuration C 1 7 heat shield forward, in the Ames 2x2 TWT

test

facility.

P

48

(60)

I

179 3.0 h = 90" 0

-.

5 -3.0 -2.5 -2.0 -1. 5 -1.0

-.

5 0 slr . 5 LO 15

Figure 21.

-

Variation of C with increasing ct

at

X = 0", X = 45", a d X = 90" at

M

= 0.9, 0.02-scale model, configuration C heat shield forward, in the Ames 2x2 TWT test facility.

P

1'

(61)

L5 LO .5 0 A = oo A = 45" A = W O 0 0

-.

5 -1.0 i i i ' 1.5 2.5 2.0 3.0 ~ -3.0 -2.5 -1.0 -1.5 -2.0

-.

5 0 slr

Figure 22. - Variation of C with increasing cr

at

X =

O",

X = 45", and X = 90"

at

C1,

TWT

test

facility.

P

(62)

1.5 L O .5 0 0 0

-.

5 a 0 140 0 150 0 160 A 170 o 180 h - O D cP h

-

45" h = wo i

k

ci- 1.5 -2.5 -1.5 0 slr .5 1.0 2.0 -2 0 -1.0

Figure 23. - Variation of C with increasing CY at X = 0 O, X = 45 O, and

h = 90 at M = 1.2, 0.02-scale model, configuration C1, heat shield

forward, in the Ames 2 X 2 T W T test facility.

P

(63)

h

-

0"

cp

A = 45" A - % a 1 5 LO .5 0 0 0 - c 0 .5 slr I ! ! ! ! L O L 5 2 0 2 5 3.0

Figure 24.

-

Variation of C with increasing cy at h = 0 O7 h = 4 5 O7 and

P

h = 90 a t M = 1 . 3 4 , 0.02-scale model, configuration C1, heat shield forward, in the Ames 2 X 2 TWT test facility.

(64)

h = oo cP h = 45O h = 9 O 0 2 0 L 5 LO .5 0 0 0

-.

5 a 0 140 0 150 0 160 A 170 c, 180 " -3.0 -2.5 -2.0 -1.5 -1.0 -.5 0 .5 LO 1.5 2.0 2.5 3.0 slr

Figure 25. - Variation of C with increasing (Y at X = 0 O, X = 45 O, and

X = 90 at M = 1.48, 0.02-scale model, configuration C1, heat shield forward, in the JPL-2OSWT test facility.

P

(65)

i I I

i

!

i

T

f

A

-

0' "_ '. . . cP I 1 : - 0 , : . I . . A = 45O h = 90" 1 1 ' ' . F I : ' : : i I . + ., -5.0 -2.5 -2.0 -1.5 -1.0 -.5 0 slr - .5 1.0 1.5 2.0 2.5 cy at X = 0 O, X = 45 O, and

Figure 26. - Variation of C with increasing P

h = 90 O

at

M = 2.01, 0. 02-scale model, configuration C heat shield

forward, in the JPL-2OSWT test facility.

1'

(66)

a 0 140 0 150 A 170 0 168 0 180 1. ! 1. I

_k

1 .. h = O O I

t

1 I i ! I I c P I I h = 45" I , / ' I ( ' I i -3.0 -2.5 -2.0 -1.5 -1.0 -.5 0 . 5 1.0 1. 5 2.0 2.5 3.0 slr

Figure 27. - Variation of C with increasing a a t X = 0 O , X = 4 5 O, and

X = 90 at M = 3 . 0 1 , 0.02-scale model, configuration C1, heat shield forward, in the JPL-2OSWT test facility.

P

(67)

I 2.0 1.5 1.0 . 5 A Z O 0 0 c P h = 45" 0 A = 90" 0 -. 5 t . . , . . . . . -3.0 -2. 5 -2.0 -1.5 -1.0

-.

5 0 . 5 1.0 I.. 5 2.0 2.5 3.0 slr

Figure 28. - Variation of C wi.th increasing cy a t h = 0 O, X = 45 O, and

X = 90 O at M = 3.99, 8.02-scale model, configuration

Cp,

heat shield

forwsrd; in the JPL-2OSWT test facility. P

(68)

20 L 5 LO . 5 A-0' 0 ! I ! I 1 1 ' 1 1 CP I A-45O 0 A - W 0 0 - 2 5 -20 - L 5 -1.0

-.

5 0 .5 1.0 1.5 20 2.5 3.0 slr

Figure 29.

-

Variation of C with increasing Q at X = 0 O, X = 45 O, and

P

X = 90' at M = 5.01, 0.02-scale model, configuration C1, heat shield forward, in the JPL-2OSWT test facility.

(69)

2.0 1.5 LO . 5 0 0 0

-.

5

i

I I I I I ~ I

l

I

!

I I i I ! i

I

i

~

i

E a 140 150 160 170 180 A = oo c P A = 45" A = 90" I 1.0 L 5 2.0 -2.5 '

Figure 30.

-

Variation of C with increasing CY

at

h = 0 O, X = 45 O,

and X = 90 a t M = 6.07, 0.02-scale model, configuration C1, heat shield forward, in the JPL-21HWT test facility.

P

(70)

-L 5 -L 0 .5 0

slr

.5 LO L 5 2 5 2 0 3.0

Figure 31. - Variation of C with increasing LY a t X = 0 O, h = 45 O,

P

and h = 9 0 a t M = 7 . 3 5 , 0.02-scale model, configuration C heat shield forward, in the JPL-21HWT test facility.

1'

(71)

2.0 1.5 1.0 .5 A - O 0 0 a o 140 0 150 0 MI D 170 b 180 c P ! h-45O 0

i::::,

. LL::

.

: ' I ! i I O , I,/# I . . A = 90" 0

-.

5 , . I 1 1 3.0 -2.5 -2.0 -1.5 -1.0 -.5 0 . 5 1.0 1.5 2.0 2.5 3.0 slr

Figure 32. - Variation of C with increasing cy a t X = 0 O, X = 45 O, and

X = 9 0 O at M = 9.08, 0.02-scale model, configuration C1, heat shield

'forward, in the JPL-21HWT test facility. P

(72)

I

h

-

oo CP h

-

4 5 O h - 9 0 " 2.0 L5 LO .5 0 0 / I I 1 , slr . . I I . ! ' I '

Figure 33. - Variation of C with increasing cr at X = 0 O, X = 45 O, and

X = 9 0 at M = 10. 1, 0. 045-scale model, configuration C2, heat shield forward, in the AEDC-C test facility.

P

(73)

h

-

0" 25 2 0 L5 LO .5 0 0 0 - . 5 , rlr

Figure 34. - Variation of C P with increasing

a

at X =

O",

X = 45 O, and X = 90 O

at

M = 12.0, 0.05-scale model,

configuration

C2,

heat shield forward, in the CAL-48HST test facility.

(74)

CP h

-

45" h

-

9oo 2 0 1.5 LO . 5 0 -. 5 -L -1.0 I I

ll

_-.

5 I 0 S l I / IC: 1.0 1.5 21 5

Figure 35. - Variation of Cn with increasing a a t h = O O , h = 4 5 " , and h = 9 O 0 a t M = 1 2 . 7 , 0.05-scale model, configuration C2, heat shield

r

5 180

~

3.0

forward, in the CAL-48HST test facility.

(75)

[I 0 152 0 160 I I !. ( I ' ! ! I .t , . , ' I : / I

i ;

i !

' ! 9 o o 0 -. 5 A = I I ! -2.0 -1.5 .5 1.0 1.5 2.0 2.5 3.0 a t X = 0 O, 0 s l r Figure 36. - Variation of C P with increasing cr

X = 45 O, and X = 9 0 O a t

M

= 1 3 . 1 , 0.05-scale model,

configuration C 2 , heat shield forward, in the CAL-48HST test facility.

(76)

cP 2.0 1.5 1.0 .5 h-0" 0 h - 4 5 O 0 h - 9 0 " 0 . 5 1.0 I I a 0 152 0 160 A 180 1.5 2.0 2.5 3.0

Figure 37. - Variation of C with increasing Q at

P

X = 0", X = 45

",

and X =-go" at M = 1 6 . 2 , 0.05-scale model, configuration C2, heat shield forward, in the CAL-48HST test facility.

(77)

A -0" CP -1.0 -.5 .5 , ; I , . .

-

1.5 2.0 25 3.0

Figure 38. - Variation of C with increasing a a t X = 0 O,

P

X

= 45 O, and X = 90 Oat M = 1 7 . 3 , 0.05-scale model,

configuration

C2,

heat shield forward, in the CAL-48HST test facility.

(78)

2.0 1.5 1.0 .5 0 h =ao r I cP h = 45' ! I , I I 1 i I I i I I 1 1

I

.5 slr h = 9 o o NASA-Langley, 1969 - 1

I

0 0 - G

..

.1.! 5 Figure -1.0

-.

5 9. - Vari; 1.0 incrc 1.5 3 . 0

c

w

P

X = 0 O, X = 45 O, and X = 90" at M = 19.0, 0.04-scale model, configuration

C2,

heat shield forward, in the AEDC-HS 11 test facility.

wing a at

(79)

NATIONAL AERONAUTICS A N D S P A C E ADMINISTRATION

WASHINGTON, D. C. 20546

OFFICIAL BUSINESS FIRST CLASS MAIL

NATIONAL AERONAUTICS ANI

POSTAGE AND FEES PAID SPACE ADMINISTRATION

”

NASA SCIENTIFIC AND TECHNICAL PUBLICATIONS

TECHNICAL REPORTS: Scientific and technical information considered important, complete, and a lasting contribution to existing knowledge.

TECHNICAL NOTES: Information less broad in scope but nevertheless of importance as a contribution to existing knowledge. TECHNICAL MEMORANDUMS: Information receiving limited distribution because of preliminary data, security classifica- tion, or other reasons.

CONTRACTOR REPORTS: Scientific and technical information generated under a NASA contract or grant and considered an important contribution to existing knowledge.

TECHNICAL TRANSLATIONS: Information published in a foreign language considered to merit NASA distribution in English. SPECIAL PUBLICATIONS: Information derived from or of value to NASA activities. Publications include conference proceedings, monographs, data compilations, handbooks, sourcebooks, and special bibliographies. TECHNOLOGY UTILIZATION

PUBLICATIONS: Information on technology

used by NASA that may be of particular

interest in commercial and other non-aerospace xpplications. Publications include Tech Briefs, Technology Utilization Reports and Notes, and Technology Surveys.

Details on the availability of these publications may be obtained from:

SCIENTIFIC AND TECHNICAL INFORMATION DIVISION