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AEDO-TR-78-4 AFATL-TR-77-110

, : I

-~ • 11t;,~" ; G 1978 4 . . . I ' t

- ' - ,-'1' AUG 1 5 1985

RESULTS OF A WIND TUNNEL AND FLIGHT TEST PROGRAM

TO DEVELOP A MAXIMUM VOLUME BOMB [MVB)

CONFIGURATION FOR MULTIPLE CARRIAGE

AND SEPARATION PROM TACTICAL

AIRCRAFT AT MACH NUMBERS

FROM 0.50 TO 1.10

David W. Hill, Jr. ARO, Inc., a Sverdrup Corporation Company

PROPULSION WIND TUNNEL FAC~t.ITY ARNOLD ENGINEERING DEVELOPMENT CENTER

AIR-FORCE SYSTEMS COMMAND ,ARNOLD AIR FORCE STATION, TENNESSEE 37389

May 1978

Final Report for Period February 4, 1975 -.May 21, 1976

TECHNICAL REPORTS FILE COPY.

Approved for public release; distribution unlimited.

Prepared for

AIR FORCE ARMAMENT LABORATORY/DLJC EGLIN AFB, FLORIDA 32542

; , , T* > , . .

I r l e

• e . y . "

m W

, . ~ ~ . ~ .-~

NOTICES

When U. S. Government drawings, specifications, or other data are used for any purpose other than a definitely related Government procurement operation, the Government thereby incurs no responsibility nor any obligation whatsoever, and the fact that the Government may have formulated, furnished, or in any way supplied ~e said drawings, specifications, 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 manufacture, use, or sell any patented invention that may in any way be related thereto.

Qualified users may obtain copies of this report from the Defense Documentation Center.

References to named commerical 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.

This report has been reviewed by the Information Office (01) and is releasable to the National Technical Information Service (NTIS). At NTIS, it will be available to the general public, including foreign nations.

APPROVAL STATEMENT

This report has been reviewed and approved.

JAMES M. McGEE, 2d Lt, UgAF Test Director, PWT Division Directorate of Test Operations

Approved for publication:

FOR THE COMMANDER

D oo or of D Deputy for Operations

UNCLASSIFIED - READ [ N S T R U C T | O N S

REPORT DOCUMENTATION PAGE BEFORE COMPLETING FORM I R I E P O R " N J M g E R ~2 G O V T ACCESSION NO. 3 RECIP 'F_N~"S C A T A L O G N U M B E R

AEDC-TR-78-4 AFATL-TR-77-110 i

4 TITLEtmdSub~,tJe) RESULTS OF A WIND TUNNEL AND FLIGHT TEST PROGRAM TO DEVELOP A MAXIMUM VOLUME BOMB (MVB) CONFIGURATION FOR MULTI- PLE CARRIAGE AND SEPARATION FROM TACTICAL AIRCRAFT AT ~CH NU~ERS FROM 0.50 TO 1.10

7 A~ T H O R f s ;

David W. H i l l , J r . , AHO, I n c .

9 P E R r O R M , N G O R G A N I Z A T I O N N A M E AND ADDRESS

A r n o l d E n g i n e e r i n g D e v e l o p m e n t C e n t e r / D O Ai r F o r c e S y s t e m s Command 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 37389

11 C O h T R O L L I N G O f F CE N A M E A N D A D D R E S S

A i r F o r c e Armament L a b o r a t o r y / D L J C E g l i n AFB, F l o r i d a 32542

14 M O h I T O R I h G A G E N C V N A M E & ADDRESS 'J r dl l feeenf I rom Con: to ! i tnO Of. t ics)

TYPF., O F ~ R E P O m T , & P~RJ OD C O V E R E I ~ l n a - ~ e p o r c - y e D r u a r y ~,

1975 - May 21, 1976

S P E R F O R M I N G ORG R E P O R " N U M B E R

8 C O N T R A C T O R G R A N ~ N.JM,31ERr~)

10. P R O G R A M E L E M E N T P R O J E C T T A S K A R E A & WORK U N I T h i - M B E R S

Prog ram E lemen t 62602F P r o j e c t 2567 , Task 02 tZ R E P O R T D A T E

May 1978 t3 N U M B E R O F P A G E S

173 15 S E C U R I T Y CLASS (o f rh is repor t )

UNCLASSIFI'ED

1So D E C L ASSI r I C A T I O N ' DOWP, G R A D I N G S C H E D U L E N/A

16 D ' S T R I B U T ON S T A T E M E N T Rot t h i s RepotS)

A p p r o v e d 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 .

t7 D I S T R I B U T I O h S T A T E M E N T .'o[ the abs t rec f ente red in BJock 20. I I d t l f e ren f from Rspo t f )

t8 S U P P L E M E N T A R Y ROTES

Available in DDC

' 9 K E Y WOR~S {C~nfJns.e on t o y s , s o s ide t l nece~sat~ ~ JdenfJfy ~ bJock number)

wind t u n n e l t e s t s s e p a r a t i o n f l i g h t t e s t i n g Mach numbers maximum vo lume bomb (MVB) F-4C a i r c r a f t c a r r i a g e s A-7D a i r c r a f t

s t a t i c s t a b i l i t y d y n a m i c s s t a b i l i t y

20 A B S T R A C T {ContJnue on reve rse s ide Jf n e c e s s a r y ~ d Jden t l f y ~ bJock n u m b e ~

Wind t u n n e l t e s t s , s u p p o r t e d by f l i g h t t e s t d a t a , w e r e c o n d u c t e d i n o r d e r t o d e t e r m i n e s e p a r a t i o n c h a r a c t e r i s t i c s o f a 1 6 - i n . - d i a m maximum vo lume bomb (~fVB) f rom the i n b o a r d - p y l o n t r i p l e e j e c t i o n r a c k (TER) on t h e F-4C a i r c r a f t . The wind t u n n e l t e s t s w e r e c o n d u c t e d in t h e A e r o d y n a m i c Wind T u n n e l s (1T) and (4T) o f t h e P r o p u l s i o n Wind Tunne l F a c i l i t y (P%'T) t o o b t a i n s t a t i c and dynamic s t a b i l i t y d a t a on t h e s t o r e in t ~ e f r e e s t r e a m , and

FORM 1 4 7 3 E D I T , O N O F , N O V 6 S , S O O S O L E T E D D , JAN ,3

UNCLASSIFIED

UNCLASSIFIED

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

c a p t i v e t r a j e c t o r y d a t a on t h e s t o r e when r e l e a s e d f r o m t h e F -4C and A-7D a i r c r a f t . The f i n s o f t h e .M~B w e r e c a n t e d f r o m 0 t o - 1 2 d e g , w i t h and w i t h o u t f i n t a b s , t o a s s e s s t h e i r e f f e c t i v e n e s s i n r e d u c i n g t h e s e v e r e n o s e - d o w n p i t c h m o t i o n e n c o u n t e r e d d u r i n g s e p a r a t i o n a t h i g h s u b s o n i c ~ c h n u m b e r s . The t e s t s w e r e c o n d u c t e d a t Mach n u m b e r s f r o m 0 . 5 0 t o 1 . 1 0 a t s i m u l a t e d p r e s s u r e a l t i t u d e s o f 5 , 0 0 0 a n d 2 0 , 0 0 0 f t . The w i n d t u n n e l t e s t s i n d i c a t e d , a t a l l Mach n u m b e r s , t h a t t h e n o s e - d o w n p i t c h m o t i o n o f t h e s t o r e was s i g n i f i c a n t l y r e d u c e d b y c a n t i n g t h e f i n s . H o w e v e r , t h e f l i g h t t e s t s a t Mach n u m b e r 0 . 9 0 i n d i c a t e d t h a t t h e s e v e r e n o s e - d o w n p i t c h m o t i o n c o n t i n u e d e v e n w i t h t h e c a n t e d f i n s . The i n - f l i g h t f i l m d a t a s h o w e d t h a t c o l l i s i o n o c c u r r e d b e t w e e n t h e MVB t a i l - f i n t a b s a n d t h e f i n s o f t h e a d j a c e n t s t o r e s . T h i s " h a n g - u p " o f t h e t a i l f i n s r e s u l t e d i n a p i v o t a l , o r c o n s t r a i n e d , m o t i o n up t o - 4 0 d e g p i t c h a n g l e .

A l . ~ { A - ~ ! * ,FS " r , - n

UNCLASSIFIED

" ~ A E D C - T R - 7 8 - 4

PREFACE

The work reported herein was conducted by the Arnold Engineering Development

Center (AEDC), Air Force Systems Command (AFSC), at the request or" the .Air Force Armament Laboratory (AFATL/DLJC), AFSC, under Program Element 62602F, Project

2567, Task 02. The AFATL project monitor was Maj. R. Van Putte. The results were obtained by ARO. Inc.. AEDC Division (a Sverdrttp Corporation Company), operating contractor for the AEDC, AFSC, Arnold Air Force Station, Tennessee. The tests were

conducted under ARO Project No. P41G79A. Data reduction was completeci in January 1977, and the manuscript was submitted for publication on December 21, 1977.

A E D C -T R -78-4

CONTENTS

Page

i.0 INTRODUCTION ................................. 9

2.0 APPARATUS

2.1 Test Facility ................................. 10

2.2 Test Articles ................................. 1 ! 2.3 Instrumentation ............................... 12

3.0 TEST DESCRIPTION

3.1 Test Conditions ............................... 13

3.2 Dynamic Stability Data Acquisition . . . . . . . . . . . . . . . . . . . . . 13

3.3 Static Stability Data Acquisition . . . . . . . . . . . . . . . . . . . . . . . 13

3.4 "Trajectory Data Acquisition . . . . . . . . . . . . . . . . . . . . . . . . . 13

3.5 Corrections .................................. 14

3.6 Precision of Data ............................... 14

4.0 RESULTS AND DISCUSSION

4.1 Static Stability Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 4.2 Aerodynamic Data in the F-4C Aircraft Flow Field . . . . . . . . . . . . . 17

4.3 Separation Trajectories from the F-4C Aircraft . . . . . . . . . . . . . . . 17

4.4 Separation Trajectories from the A-7D Aircraft . . . . . . . . . . . . . . . 18

4.5 Wind Tunnel and Flight Test Separation Trajectories

from the F-4C ,Mrcraft . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

4.6 Dynamic Stability Data . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

5.0 SUMMARY OF RESULTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

REFERENCES .................................. 23

ILLUSTRATIONS

Figure

1. Typical Store Separation Installation and a Block

Diagram of the Computer Control Loop . . . . . . . . . . . . . . . . . . . . . 25

2. Tunnel 4-1" Test Section Showing Aircraft Model Locations . . . . . . . . . . . 26

3. Tunnel Test Section and Installation Details of

the 0.25-Scale MVB Model . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

4. Tunnel IT Dynamic Damping Rig Showing Installation

of 0.075-Scale MVB ................................ 29

5. Aircraft Models .................................. 30

6. Details of the Aircraft Pylons . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

7. Details and Dimensions of the Aircraft TER Models . . . . . . . . . . . . . . . 34

3

AE DC-TR-78-4

Figure Pag_.~e

8. Details and Dimensions of the A-7D MER Model . . . . . . . . . . . . . . . . 36

9. Details and Dimensions of the F-4C Outboard 370-gal

Fuel Tank Model ................................. 37

10. Details and Dimensions of the 0.05-Scale MVB Model . . . . . . . . . . . . . . 38

11. Tunnel 4T Installation Photograph of F-4C Aircraft,

MVB. and CTS .................................. 39

12. Details and Dimensions of tile 0.25-Scale MVB Model . . . . . . . . . . . . . . 40

13. Tunnel 4T Installation Photograph of 0.25-Scale

MVB Model .................................... 42

14. Tunnel IT Installation Photograph of 0.075-Scale

MVB Model with Interchangeable Tails . . . . . . . . . . . . . . . . . . . . . . 43

15. Installation Photograph of Full-Scale MVB on

TER and F-4C Aircraft . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44

16. MER and TER Store Stations and Orientations . . . . . . . . . . . . . . . . . 46

17. Comparison of Wind Tunnel 0.25-Scale MVB Static

Stability Data with Predicted Data of CAMS . . . . . . . . . . . . . . . . . . . 47

18. Effects of Fuze, Tabs, and Fins on the 0.25-Scale

MVB Static Stability ............................... 51

19. Effects of Fuze and Tabs on the MVB Static Stability,

Fins Canted .................................... 55

20. Effects of Model Scale on the Static Stability of

the MVB, Fins Canted ............................... 59

21. Effects of Reynolds Number on the MVB Static Stability . . . . . . . . . . . . 62

22. Aerodynamic Characteristics of the MVB in the F-4C

Flow Field, Fins Uncanted . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66

23. Aerodynamic Characteristics of the MVB in the F-4C

Flow Field, Fins Canted . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ' . 69

24. Variation of the Aerodynamic Coefficients of the

MVB with Fin Cant Angle, Two Fins Canted . . . . . . . . . . . . . . . . . . . 73

25. Variation of the Aerodynamic Coefficients of the ,

MVB with Fin Cant Angle, Four Fins Canted . . . . . . . . . . . . . . . . . . 74

26.

27.

Wind

from

Four

Wind

from

Two

Tunnel Separation Trajectories of the MVB

the No. 1 TER Station of the F-4C Aircraft.

Fins Canted ................................. 75



Fins Canted ................................. 83

A E D C-T R -78-4

Figure I>a ge

28. Wind

from

Two

29. Wind

from

Two

30. Wind



Fins Canted ................................. 91


the No. 3 TER Station of the F-4C Aircraft,

Fins Canted ................................. 95 • . (

Tunnel Separation TraJectories of the MVB

with Simulation of Fhls Returned from -12 to 0 deg

duri,lg the Trajectory ............................... 99

31. Illustration of MVB Trajectories with Si,nulation

of Fins Returned from -12 to 0 deg Cant . . . . . . . . . . . . . . . . . . . . 103

32. Wind Tunnel Separation Trajectories of the MVB

from the A7-D Aircraft at M = 0.90 . . . . . . . . . . . . . . . . . . . . . . . 105

33. Wind Tunnel Captive Trajectory and Flight Test

Separation Trajectories of the MVB with Uncanted

Fins, M** = 0.50 .................................. I 15

34. Illustration of Wind Tunnel Captive Trajectory and

Flight Test Separation Trajectories of the MVB

with Uncanted Fins, M** = 0.50 . . . . . . . . . . . . . . . . . . . . . . . . . . 119

35. Release Sequence of the MVB with Uncanted Fins, No

Tabs, M** = 0.50 .................................. 120



Fins, M.. = 0.70 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 121



with Uncanted Fins, M** = 0.70 . . . . . . . . . . . . . . . . . . . . . . . . . . 123


Separation Trajectories of the MVB with Canted

Fins, M. = 0.70 .................................. 124



with Canted Fins, M** = 0.70 . . . . . . . . . . . . . . . . . . . . . . . . . . . 126

40. Release Sequence of the MVB at M~ = 0.70 . . . . . . . . . . . . . . . . . . . . 127



Fins, M** = 0.90 .................................. 128

A E D C-T R -7 8-4

Figure



with Uncanted Fins, M= = 0.90 . . . . . . . . . . . . . . . . . . . . . . . . . . 130


Separation Trajectories of the MVB with Canted

Fins, M** = 0.90 .................................. 131



with Canted Fins, M= = 0.90 . . . . . . . . . . . . . . . . . . . . . . . . . . . 133


Separation Trajectories of the MVB with Can~ed

Fins and Tabs. M** = 0.90 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 134



with Canted Fins and Tabs, M= = 0.90 . . . . . . . . . . . . . . . . . . . . . . 136

47. Release Sequence of the MVB at M= = 0.90 . . . . . . . . . . . . . . . . . . . 137



Fins, No. 1 TER Station, M = 1.02 . . . . . . . . . . . . . . . . . . . . . . . 138

49. lUustration of Wind Tunnel Captive Trajectory and


with Uncanted Fins, No. 1 TER Station, M= = 1.02 . . . . . . . . . . . . . . . 140



Fins, No. 2 TER Station, M ~ 1.02 . . . . . . . . . . . . . . . . . . . . . . . . 141

51. Release Sequence of the MVB with Uncanted Fins, No

Tabs, M** = 1.02 .................................. 143

52. Effects of Angle of Attack on the Pitch-Damping

Derivative of the MVB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 144

TABLES

I. Full-Scale Store Parameters . . . . . . . . . . . . . . . . . . . . . . . . . . . . 146

2. Identification of Captive Trajectory Test Configurations

and Test Conditions for F-4C Aircraft . . . . . . . . . . . . . . . . . . . . . . 14i

3. Identification of Captive Trajectory Test Configurations

with Test Conditions for A-7D Aircraft . . . . . . . . . . . . . . . . . . . . . . 153

6

A E D C-T R -78 -4

TABLES (Continued)

4. Identification of Static Stability Test Conditions

for the 0.05-Scale MVB Model . . . . . . . . . . . . . . . . . . . . . . . . . . 158

5. Identification of Static Stability Test Conditions

for the 0.25-Scale MVB Model . . . . . . . . . . . . . . . . . . . . . . . . . . 161

6. Dynamic Stability Test Configurations and Test

Conditions for the 0.075-Scale MVB Model . . . . . . . . . . . . . . . . . . . 168

7. Typical Uncertainties for Force and Moment Coefficient

Data and Trajectory Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 169

NOMENCLATURE ................................ 170

A E DC -T R -78 -4

1.0 INTRODUCTION

Store separation problems have been encountered during release of large diameter

stores from the triple ejection rack (TER) oll the inboard pylon of the F-4C aircraft. The

maximum store diameter is limited to approximately 16 in. for multiple carriage on the

TER. The most rapid nose-down pitch motion occurs for release from the bot tom station

of the TER at Mach numbers greater than 0.70. The excessive nose-down pitch is

undesirable, and in some cases unacceptable, from the standpoint of aircraft safety and

munition delivery. Previous wind tunnel tests have shown that there is a large pressure

buildup in the nose cavity region of the cluster of three stores, and an upwash flow field

near the store afterbody. The resulting curvilinear flow field over the store is somewhat

decreased as the store diameter is decreased from 16 to 12 in. In fact, 12-in.-diam stores

have been successfully released (Rel: 1) up to Mach number 1.20. tlowever, the purpose

of carrying 16-in.-diam stores is to provide maximum payload for the aircraft. As a result

of the stm~s being closely clustered, there is mininaal space for providing a large fin area

to increase the static stability of the store. Solne 16-in.-diam weapons contain "pop-out"

fins for deploylnent after the store is released, but the increased static inargin is to little

avail as the store nose-down angular acceleration is too great to be overcome. There has

been one wind tunnel test in which the TER geometry was modified to allow better flow

characteristics around the adjacent stores, but these modifications did not show much improvement on the separation trajectories.

The Air Force Armament Laboratory (AFATL) sponsored "a program for tile

aerodynamic design of a 16-in.-diam store that would separate from the TbR station

without severe nose-down pitch nlotion~---The-store would generally be used for a

munition dispenser. Tile design requirements for the store were to be the following:

Aircraft release Mach number

Aircraft release altitude

Store length (including fuze)

Store diameter

Maximum fin span

Hemispherical nose radius

Store weight

Moment of inertia

Center-of-gravity location from nose (without fuze)

0.90

5,000 ft

92 in.

16 in.

22 in.

8 in.

800 ib

65 slug-ft 2

36.5 in.

AE DC-TR-78-4

These dimensions were selected to provide maximum payload when installed on a TER.

Henceforth in this report, the store designed to these criteria will be referred to as the

maximum volume bomb (MVB).

After review of past wind tunnel data, it appeared that successful release over the

complete speed range would require the imposition of a compensating nose-up moment

on the store during ~the initial release motion. The amount of tile required moment varied

directly with the 'magnitude of the offending aerodynamic moment. It was thus

concluded that the best approach would be to use aerodynamic means to provide the

compensating forces. The solution suggested by the present evaluation was to utilize the

tail fins (needed anyway for basic aerodynamic stability) to generate the necessary loads.

The tail fins would be rotated (canted) to a leading-edge-down attitude while the store is

carried on the rack and during the initial release period. When the store has moved a

short distance away from the rock (approximately one body diameter), the fins would be

returned by a lanyard to the normal symmetric position. Wind tunnel and flight tests

were conducted to determine if this technique were feasible.

The wind tunnel tests were conducted in the Aerodynamic Wind Tunnel (4T)

(Tunnel 4T) of the Propulsion Wind Tunnel Facility (PWT). The aerodynamic loads test,

dynamic stability test. and captive trajectory tests covered a Mach number range from

0.50 to 1.10. The simulated flight altitude for the captive trajectory" tests was 5,000 ft.

The flight tests were conducted at Eglin AFB and covered a Mach number range from

0.50 to 1.02, with a release altitude of 5,000 ft.

2.0 APPARATUS

2.1 TEST FACILITY

Tunnel 4T is a closed-loop, continuous flow, variable density tunnel in which the

Mach number can be varied from 0.10 to 1.30. At all Mach numbers, the stagnation

pressure can be varied from 300 to 3,700 psfa. The test section is 4 ft square and 12.5 ft

long with perforated, variable porosity (0.5- to 10-percent open) walls. It is comple.tely

enclosed in a plenum chamber from which the air can be evacuated, allowing part of

the tunnel airflow to be removed through the perforated walls of the test section. A

more thorough description of the tunnel is given in Ref. 2.

The Aerodynamic Wind Tunnel (1T) (Tunnel IT) of PWT is a continuous flow wind

tunnel capable of being operated at Mach numbers from 0.20 to 1.50 utilizing variable

nozzle contours above M.. = 1.00. The tunnel is operated at a stilling chamber total

pressure of approximately 2.850 psfa. The test section is 1 ft square and 3.13 ft long

10

A E DC-TR-78-4

with six-percent-open area. inclined, perforated walls. A more thorough description of the

tunnel is given in Ref. 2.

For store separation testing in Tunnel 4T, two separate and independent support

systems were used to support the models. The aircraft model was inverted in the test

section and supported by an offset sting attached to the main pitch sector. The store

model was supported by the captive trajectory support (CTS) which extends down from

the tunnel top wall and provides store movement (six degrees of freedom) independent of

the aircraft model. An isometric drawing of a typical store separation installation is

shown in Fig. 1.

Also shown in Fig. 1 is a block diagram of the computer control loop used during

captive trajectory testing. The analog system and the digital computer work as an

integrated unit and. utilizing required input information, control the store movement

during a trajectory. Store positioning is accomplished by use of six individual d-c electric

motors. Maximum translational travel of the CTS is -+ 15 in. from the tunnel centefline in

the lateral and vertical directions and 36 in. in the axial direction. Maximum angular

displacements are -+45 deg in pitch and yaw and -+360 deg in roll. A schematic showing

the test section details of the models in the tunnel is shown in Fig. 2.

For static force testing in Tunnel 4T, the model support system consisted of a pitch

sector strut and sting attachment which had a pitch capability o f - 6 to 26 deg with

respect to the tunnel centerline and a roll capability o f -180 to 180 deg with respect to

the sting centerline. A schematic of the test section showing the location of the models is

presented in Fig. 3.

For dynamic testing in Tunnel IT, the model support system consisted of a sting

attached to a free-oscillation meclaanism mounted on top of the test section. The model

was mounted on a circular strut perpendicular to the model longitudinal axis and through

the center of gravity. The pitch capability of the mechanism was -90 to 90 deg with

respect to the tunnel centerline. A schematic of the n~echanism and location of the

model is shown in Fig. 4.

2.2 TEST ARTICLES

For CTS testing, the test articles were 0.05-scale models of the MVB and the A-7D

and F-4C aircraft. Because of interference with the CTS sting, the horizontal stabilizers of

both aircraft models were remo~.ed for these tests. Dimensional sketches of the F-4C and

A-7D aircraft models are shown in Fig. 5. Details and dimensions of the pylon, TER,

MER, and 370-gal fuel tank models are shown in Figs. 6 through 9. Details and

11

A'E DC-TR-78-4

dimensions of the 0.05-scale MVB model used for trajectory testing are shown in Fig. 10.

The 5- and 8-in. hinge lines are noted in the figure. For the 5-in. hinge line, the four

tail-fin root chords were contoured to fit the boattail (no gap), whereas with the 8-in.

hinge line the tail-fin root chord was straight and the fin was mounted directly (gap) to

the boattail body by means of the hinge. Figure 11 is a photograph showing the

0.05-scale MVB installed on the CTS sting and the installation of the F-4C aircraft.

Details and dimensions of the 0.25-scale MVB model used for static stability testing

are shown in Fig. 12. The tail fins were mounted at the 5-in. hinge line, and

interchangeable fins were provided so that varying gap configurations could be simulated.

Figure 13 is a photograph showing the 0.25-scale MVB installation.

Figure 14 is a photograph showing the 0.075-scale MVB model installed for dynamic

stability testing in Tunnel IT, along with the various interchangeable afterbody sections.

Figure 15 is a photograph showing the full-scale MVB installed on the TER of the F-4C

aircraft.

2.3 INSTRUMENTATION

For CTS testing, a 0.3-in.-diam, six-component, internal strain-gage balance was used

to obtain the force and moment data on the MVB model. The F-4C and A-'7D aircraft

angle of attack was set using a gravimetric angular position indicator located in the nose

of each aircraft model. Translational and angular positions of the store model were

obtained from the CTS analog inputs. The pylons and racks were instrumented with

touch wires to indicate when the MVB model was in its carriage position. The system was:

also electrically connected to automatically stop the CTS and main pitch sector

movements if the store or CTS rig contacted the aircraft model, sting, or the test section

walls.

For static stability testing, a 0.8-in.-diam, six-component balance was used to

measure the MVB aerodynamic loads.

The dynamic stability tests used the free-oscillation technique, and the model

position was measured with a strain-gaged beam. A signal proportional to model

oscillation amplitude was conditioned and recorded on an oscillograph, on a damping

system that instantaneously records cycles to decay to one-half amplitude, and on

magnetic tape for offline data reduction. Model angle of attack was measured with a

linear potentiometer which was mounted between the inner and outer shells of the test

mechanism. All of the online signals were input into a digital computer for reduction to

aerodynamic coefficients.

12

A E D C-T R -7 8 -4

3.0 TEST DESCRIPTION

3.1 TEST CONDITIONS

Separation trajectory data were obtained at Math numbers from 0.50 to 1.10.

Tunnel dynamic pressure ranged from 200 psi" at M= = 0.50 to 1,200 p s f a t M= = 1.10,

and tunnel stagnation temperature was maintained near 90 *F.

Tunnel conditions were held constant at the desired Mach number and stagnation

pressure while data for trajectory, static stability, and dynamic stability were obtained.

The trajectories were terminated when the store or sting contacted the aircraft model or

a CTS limit was reached. The static stability data acquisition was terminated when the

desired angle-of-attack range was obtained. The dynamic stability data acquisition was

terminated when sufficient model oscillation frequency data were obtained. Full-scale

store parameters of the MVB used in the wind tunnel trajectories are listed in Table 1.

Configurations and lest conditions are listed in Tables 2 through 6.

3.2 DYNAMIC STABILITY TEST DATA ACQUISITION

The model was initially deflected to 4 deg and then released. During the decay

period, data were recorded on a damping meter and a magnetic tape system. An

oscillograph was used to monitor the balance system. Data points at a given test

condition were continued until repeatability was observed.

3.3 STATIC STABILITY DATA ACQUISITION

After the desired test conditions were established in the tunnel, control o f the MVB

model support was switched to the automatic model att i tude positioning system

(AMAPS). The AMAPS is a computer-controlled systeln which atttomatically steps the

model through u preprogrammed sequence of model attitudes and takes data at each set

position. Model pitch and roll angles were used by the AMAPS to generate combinations

,of angle of attack and sideslip. Model parameters used in the reduction of lbrce and

moment data to aerodynamic coefficients are'presented in Table I.

3.4 TRAJECTORY DATA ACQUISITION

To obtain a trajectory, test conditions were established in the tunnel and the aircraft

model was positioned at the desired angle of attack. The store model was then oriented

to a position corresponding to the store carriage location. After the store was set at the

desired initial position, operational control of the CTS was switched to the thgital

computer which controlled the store movement during the trajectory through comlnand~

13

AE DC-TR-78-4

to the C~S analog system (see block diagram, Fig. 1). Data from the wind tunnel,

consisting of measured model forces and moments, wind tunnel operating conditions, and

CTS fig positions were input to the digital computer for use in the full-scale trajectory

calculations.

The digital computer was programmed to solve the six-degree-of-freedom equations

to calculate the angular and linear displacements of the store relative to the aircraft

pylon, in general, the program involved using the last two successive measured values of

each static aerodynamic coefficient to predict the magnitude of the coefficients over the

next time interval of the trajectory. These predicted values were used to calculate the

new position and attitude of the store at the end of the time interval. The CTS was then

commanded to mo~.e the store model to this new position, :rod the aerodynamic loads

were measured. If these new measurements agreed with the predicted values, the process

was continued over another time interval of the same magnitude. If the measured and

predicted values did not agree within the desired precision, the calculation was repeated

over a time interval one-half the previous value. This process was repeated until a

complete trajectory had been obtained.

in applying the wind tunnel data to the calculations of the full-scale store

trajectories, the measured forces and moments were reduced to coefficient form and then

applied with proper full-scale store dimensions and flight dynamic pressure. Dynamic

pressure was calculated using a flight velocity equal to the free-stream velocity

component plus the components of store velocity relative to the aircraft, and a density

corresponding to the simulated altitude.

The initial portion of each launch trajectory incorporated simulated ejector forces in

addition to the measured aerodynamic forces acting on the store. The ejector force was

considered to act perpendicular to the rack or pylon mounting surface. The locations of

the applied ejector forces and other full-scale store parameters used in the trajectory

calculations are listed in Table 1.

3.5 CORRECTIONS

Balance, sting, and support deflections caused by the aerodynamic loads on the

models were accounted for in the data reduction program to calculate the true model

angles. Corrections were also made for model weight tares to calculate the net

aerodynamic forces on the store model.

3.6 PRECISION OF DATA

Accuracy of the data presented was affected by such quantities as uncertainties in

setting tunnel conditions, sensitivity of the balance, and, in separation testing, the CTS

14

A E DC-TR-78-4

rig positions. Typical uncertainties in the data for both the static stability and trajectory

tests are presented in Table 7. The values presented are for the sets of conditions that

produced the largest uncertainties., and were determined for a confidence level of 95

percent. The estimated uncertainties in .Mach number and angle-of-attack setting are -+0.005 and -+0.1, respectively.

4.0 RESULTS AND DISCUSSION

Wind tunnel and flight test trajectory data were ob.tained on the MVB for deten .nining the feasibility of canting the tail fins and thus reducing the large nose-down

pitch motion during separation from the TER at the design Mach number of 0.90. To

verify that the aerodynamic data obtained during a trajectory with the 0.05-scale MVB model were representative of the fuU-scale MVB, the following data were obtained:

. Both the 0.05- and 0.25-scale models were tested in the free stream to

assess the effects of ,model scale, Reynolds number, and location of the fin hinge line on the static stability of the MVB.

2. Free-stream dynamic stability data were obtained with 0.075-scale MVB

models. These values of pitch-damping derivatives were used in the wind tunnel trajectory simulations.

/

Separation trajectory data were also obtained from the A-7D aircraft to assess the separation characteristics of the MVB from aircraft other than the F-4C.

4.1 STATIC STABILITY DATA

Static stability data for the MVB are presented in Figs. 17 through 21. Plots of.CN

versus ttg and Cm are presented for Mach numbers 0.50, 0.70, 0.90, and 1.10. Included in

the figures are effects of model size (0.05- and 0.25-scale) and Reynolds number on the

static stability of the MVB. Typical stability data are presentecl for fin roll angles of zero

and 45 deg. The roll anglo of zero deg represents the fin orientation for the MVB in the

No. 1 TER position. A complete listing of the configurations and test conditions for both the 0.05- and 0.25-scale static stability data is given in "Fables 4 and-5. Figure 17 presents the static stability data for the 0.25-scale MVB for fin cant angles of zero deg and fin roll

orientation of 45 deg, A comparison of values predicted by the CAMS computer program

(Ref. 3) with the experimental data is shown for each MiLch number. The fin planfonn

was chosen so as to give the best.static-margin over the Mach number range. Since the fin

span of the MVB-was limited (.22 in.) by the small interstore clearance .on the TER, the

tail-fin planform was varied analytically, to find the optimum static margin. The resultant tip chord length was found to be 9 in. (full scale), and this selection was verified later by

15

AE DC-TR-78-4

Gomillion (Ref. 4) in a wind tunnel test program. Figure 17 shows good agreement

between predicted and 0.25-scale experimental data for Mach numbers 0.50, 0.70, and

0.90. For Math number 1.10, the wind tunnel and predicted static stability data are

significantly different. This disagreement may be a result of the limited experimental data

in the CAMS program for that Mach number.

The 0.25-scale MVB static stability data for various tail-fin and nose configurations

are presented in Fig. 18. The fin gap, or air gap, simulates the gap between fin and body

which results from canting the fin.

Allee (Ref. 5) has shown that the addition of tabs to the base of the fins would

increase the static stability significantly. The tabs are attached to the tail-fin trailing edge

rather than the fin tip chord in order to maintain clearance between stores in the

clustered configuration on the TER. 'The tab geometry selected for the MVB was based

on the data in Ref. 5, and is shown in Fig. 12b. Figure 18 shows the static stability data

with and without fins, with and without fin tabs, and with and without the nose fuze.

For all Mach numbers, the MVB is neutrally stable without tabs and stable with tabs. The

addition of the nose fuze decreases the stability slightly. The neutral point location, Xx p,

represents the most aft location of the center of gravity to produce neutral static stability

and is evaluated at the trim condition. The data in Fig. 19 show the effect of fin tabs, FMU-56 fuze, and location of the fin hinge line on the static stability of the MVB with

two fins canted. In general, the addition of the fin tabs increases the static stability and results in trim angles of 15, 10, and 6 deg for Mach numbers 0.50, 0.70, and 0.90, respectively. The corresponding trim angles were 20, 20, and 22 deg for the fins without

tabs. At Math number 1.10, a trim condition was not achieved.

The effect of geometric scaling (ability to reproduce full-scale MVB geometry) on

the static stability of the MVB is shown in Fig. 20. The 0.05-scale model data show a

slightly decreased static stability for large negative angles of attack. The normal-force

coefficient was unaffected by the scaling. Data are presented for Mach numbers 0.70 and

0.90 for different hinge line positions for the 0.05-scale models. The effect of shifting the

hinge line forward was to reduce the static stability of the MVB. The normal-force coefficient again was unaffected.

The effects of model scale and Reynolds number variation on the static stability of

the MVB are shown in Fig. 21. For Math numbers 0.50 to 1.10, decreasing the Reynolds

number decreased the static stability of the MVB only slightly. The normal-force coefficient was insensitive to Reynolds number variation.

16

A E DC-TR-78-4

4.2 AERODYNAMIC DATA IN THE F-4C AIRCRAFT FLOW FIELD

Figures 22 and 23 present the aerodynamic coefficient data tbr the MVB at various

distances from TER station No. 1 in the aerodynamic interference flow field of the F-4C

aircraft. The data are presented for uncanted fins with and without tabs (Fig. 22) and for

two or four fins canted (Fig. 23). For the MVB model with canted fins, aerodynamic

coefficients are presented for hinge line positions of 5 and 8 in. (full scale). The data in

Fig. 22 and 23 show that increasing Math number from 0.50 to 1.10 results in an

increase in the depth of the interference flow field t'rom 'approximately 2 to 5 t't. A

comparison of Figs. 22 :rod 23 illustrates the effectiveness of the coqtrol fins in reducing

the nose-down pitching thoment (negative). The fin tabs and hinge line position had small

effects on CN and Cm, as illustrated in Fig~. 25b and c. Figures 24 and 25 present MVB

static aerodynamic coefficients as a function of fin cant angle for the 2- and 4-fin canted

conligurations at Mach numbers 0.50 to !.10 in the No. 1 TER carriage position. The

four-fins-canted configuration is more effective than the two-fins-canted configuration in

reducing the nose-down pitching moment, whereas ca,~ting either two or four fins has a small effect on the axial-force coefficient.

4.3 SEPARATION TRAJECTORIES FROM THE F-4C AIRCRAFT

Figures 26 through 30 present the separation trajectories of the 0.05-scale MVB

fl'om the No. 1 TER position of the F-4C aircraft. The data are presented for Math

numbers 0.50 to 1.10. Data showing the linear displacements of the store relative to the

carriage position and angular displacements relative to the attitude at carriage are

presented as functions of full-scale trajectory time. In addition, angular displacements are

plotted versus translational displacements with collision boundaries superimposed. The

full-scale store parameters used in the trajectory calculations are listed in Table 1.

Figure 26 presents separation trajectories of the MVB from the No. 1 TER position

with fin cant angles of 0, -3, -6, -9. and -12 deg. The data tbr zero deg cant angle

demonstrates the increasing nose-down pitch motion with increasing Math ntmlber. The

resulting motion caused a tail-fin collision or sting collision at Math numbers 0.70, 0.90,

and 1.10. The effect of increasing the cant angle was to reduce the nose-down pitch

motion. A fin cant angle of -12 deg produced trajectories that would allo~, separation at

the higher Much numbers. How.ever, at Math number 0.70 (Fig. 26b). the nose-up pitch

motion resulted in collision of the MVB with the adjacent stores on the TER. The large

nose--up motion may cause the MVB to collide later on with the aircraft. 1"o reduce this

nose-up motion at the lower Mach numbers, the MVB with two fins canted and with fin

tabs was tested. The purpose of the tabs was to increase the static margin of the MVB and produce a lower trim angle.

17

AE DC-TR-78-4

Separation trajectory data are presented in Fig. 27 for the 0.05-scale MVB from the

No. 1 TER position with two fins canted and with tabs. At the lower Mach numbers,

0.50 and 0.70, the nose-up motion is significantly reduced when compared to the tour-fin

cant. At Math number 0.9 (Fig. 27c), the MVB store separated without colliding, but at

Mach number 1.10 the tail collided with the adjacent store on the TER. The two-fin,

-12 deg cant with tabs was chosen as the tail configuration which best satisfied the design requirements.

Trajectories of the MVB with two fins canted when separated from the No. 2 and 3

TER stations, respectively, are presented in Figs. 28 and 29. For Mach numbers of 0.50

to 0.90, the store separated with acceptable pitch and yaw oscillations (no collision) for

the two-fin cant. At Mach number 1.10, for separation trajectories with the two-fin cant, the MVB appears not to recover in yaw motion.

Figure 30 presents separation trajectories of the MVB with simulation of fins

returned from -12 to 0 deg. The lanyard length which would activate a mechanism and

return the fins to zero cant angle was chosen to be 1.5 ft to provide the best separation

characteristics. Figure 31 presents an illustration of this type of trajectory at Mach number 0. 50.

4.4 SEPARATION TRAJECTORIES FROM THE A-7D AIRCRAFT

Separation trajectories of the MVB from the pylon, TER, and MER on the A-7D

aircraft with various tail-fin configurations at Math number 0.90 are presented in Fig. 32.

Only selected data for the design release Math number 0.90 are presented. Table 3

presents the other conditions tested. Table 1 presents the full-scale store parameters used in the trajectory calculations.

The trajectories for TER stations 1 and 2 and MER station 1 were abbreviated

because of aircraft model dynamics creating store-to-aircraft collisions. In general, the

MVB with canted tail fins and tabs exhibits better separation characteristics (less pitch and yaw motion) than the MVB without tabs.

4.5 tNIND TUNNEL AND FLIGHT TEST SEPARATION TRAJECTORIES FROM THE F-4C AIRCRAFT

,1

Comparisons of wind tunnel and flight test separation trajectory data of the MVB from the TER on the F-4C aircraft are presented in Figs. 33 through 51. The flight tests and wind tunnel tests were conducted with the MVB fins uncanted and canted. The

canted fins remained in the deflected position throughout the trajectories to simulate the

"fail-safe" mode. This mode ensures safe separation in the event of failure of the

18

A E D C-TR -78-4

mechanism for returning the fins to the zero deg cant position alter release. The MVB

was released at Mach numbers 0.50, 0.70. 0.90, and 1.02. The Mach number of 1.02 was

the maximum which the F-4C could attain at 5,000-ft altitude. The flight test conditions

are reported in Ref. 6. The Math number ~.as recorded from the Machmeter, the

altitude from the altimete,', and the angle of attack was computed from the aircraft gross weight and Math number.

Photographic data were obtained by a motion-picture camera located on the bot tom

of the aircraft fuselage. A chase aircraft obtained additional motion-picture data during

release. The photographic data were reduced to trajectory data (angles and displacements as functions of time) at the Air Force Armament Laboratory, Eglin AFB, Florida.

The comparison of wind tttnnel and flight test dtlta at Math number 0.50 is

presented in Fig. 33. The pitch angular motion of the MVB agrees reasonably well, but

yaw angle and vertical displacement do not. The wind tunnel trajectory data (Fig. 33a)

show that changes in Mach number of +0.02 from 0.50 have an insignificant effect on the MVB trajectory.

The effect of aircraft angle of attack on the wind tunnel separation trajectories of

the MVB is shown i1___21 Fig. 33c~ The effect of angle of attack is appreciable on the pitch

and yaw motion of the MVB but insignificant on the displacements.

A pictorial illustration of the wind tunnel and flight test trajectories of the MVB

with uncanted fins at hi** = 0.50 is shown in Fig. 34. Figure 35 presents a photographic sequence of the flight test trajectory taken from the chase aircraft camera data.

The wind tunnel and flight test trajectory dart, for the MVB with uncanted fins at

Mach number 0.70 is presented in Fig. 36. The angular and translational displacements show large discrepancies between wind tunnel and flight test. The wind tunnel data show

that the pitch motion does not recover, whereas the flight trajectory data indicate

recovery in pitch motion at approximately 19 t!cg. The effect of a small variation in

Mach number on the wind tunnel trajectories was sm:dl. A pictorial illustration of the wind tunnel and flight test trajectories of the MVB with uncallted fins tit Mach number 0.70 is shown in Fig. 37.

The wind tunnel and flight test trajectolfes of the MVB with two fins canted a t -12

deg at Mach number 0.70 are presented in Fig.'38. The comparison between the wind tunnel and flight test trajectories shows fair agreement. The effect of varying Math

number on the wind tunnel trajectories is insignificant. Canting the fins seems to be very

effective in reducing the nose-down pitch motion in the flight test trajectory. A pictorial

19

A E DC-TR -78-4

illustration of the wind tunnel and flight test trajectories for the MVB with two fins

canted at Mach number 0.70 is presented in Fig. 39. The illustration shows sufficient

clearance as a result of the nose-up pitch motion. Figure 40. shows time sequence

photographs from the chase aircraft of the separation trajectories of the MVB with and

without fins canted at Mach number 0.70. The photographs clearly illustrate the effect of

fin cant on the separation trajectories. The MVB with canted fins exhibits a large nose-up

motion because of nonrestoring pitching-moment coefficients at positive angles of attack,

and an increase in the magnitude of the coefficients at angles of attack above 20 deg (Fig. 20b).

The separation trajectories of the MVB without fins canted at Mach number 0.90

are presented in Fig. 41. The wind tunnel trajectory data are presented for pivotal motion up to -40 deg and for free motion. The pivotal motion constrains the tail of the

store at a fixed point of rotation to simulate the collision between the tail and adjacent

stores. The vertical translational displacement, Zp, and pitch angular displacement show

some disagreements between wind tunnel and flight data when plotted versus time.

However, the pitch variation with displacement (Fig. 41b) shows reasonable agreement.

The free-release wind tunnel trajectory had to be initiated at a vertical displacement Zp,

equivalent to 0.35 ft to eliminate collision of the tail with the adjacent stores on the

TER. A pictorial illustration of the MVB separation with uncanted fins for wind tunnel

and flight test at Mach number 0.90 is shown in Fig. 42. It can be seen that for both wind tunnel and flight test the rotation occurred at the tail of the MVB.

The MVB separation trajectories with two fins canted at -12 deg at Math number

0.90 for the wind tunnel and flight test is shown in Fig. 43. Presented are two wind

tunnel trajectories, one initiated at carriage position and the other at Zp = 0.35 ft. It can

be seen that the trajectory initiated at Zp = 0.35 ft is significantly different from the trajectory initiated at the carriage position (Zp = 0). Also presented are two repeat flight

test trajectories of the MVB. Although the trends of the repeat trajectories are the same,

the angular displacements, A0 and A~_~, show differences at any particular-trajectory time

of the same magnitude as the differences between wind tunnel and flight data (Fig. 43a). A pictorial illustration of the MVB trajectories with two fins canted at Mach number 0.90 is shown in Fig. 44.

The separation trajectories of the MVB with fills canted and with tabs at Mach

number 0.90 are presented in Fig, 45. The tabs were installed to increase the static

stability of the MVB and thus produce a recovery of the nose-down pitch motion. The

wind tunnel data are presented lbr free release and simulated pivotal releases with 0R =

-10, -20, and -40 deg. The pivotal release trajectories were obtained because the flight test

onboard motion-picture data indicated collision and "hanging-up" of the tabs on the tail

20

A EDC-TR-78-4

fin with the adjacent store fin tabs, thus creating a constrained motion or pivotal release

up to -40 deg. The wind tunnel data showed that with constrained motion for -20 deg or

greater, the MVB will not recover in pitch motion.

The wind tunnel trajectory data show the same trends as the flight test data except

for the yaw angular displacement, A~O. In Fig. 45b, the constrained motion with OR = -40

deg shows good agreement with the flight test trajectory. This good agreement implies

that tail collision, and thus constrai_ned motion, did occur in flight, and probably explains

why the wind tunnel free-release and flight test data did not agree. A pictorial illustration

of the wind tunnel free-release and fligh.t test trajectories._ of the MVB with canted fins

and .tabs is presented in Fig. 45. A sequence of flight test photographic data for the MVB

with (a) uncanted fins without tabs, (b) canted fins without tabs, and (c) canted fins

with .tabs is presented in Fig. 47.

The wind tunnel mad flight test trajectory data for the MVB from TIER station No. 1 with uncanted fins and without tabs at Math number 1.02 are shown in Fig. 48. Wind

tunnel trajectory data are presented for frec release and simulated constrained motions

( 0 R = -40). Wind tunnel trajectory data for aircraft angles of attack of zero and 1 deg are

also presented. Tile. wind tunnel data show__:_=._.__~that the M_V.B____trajectory is insensitive to

aircra._ft angle of. att.ack. The MVB pitch motion for the free-release condition is greater

than for-the constrained motion simulation. The flight test and wind tunnel trajectory

data show reasonable agreement when compared on the basis of displacements (Fig. 48b).

A pictorial illustration of the wind tunnel and flight test trajectories with fins uncanted

and without tabs for Mach number 1.02 is presented in Fig. 49. The figure (flight test)

illustrates the upward vertical displacement of the tail fins on separation, thus producing a possible collision with adjacent store tail fins.

The separation trajectory data of the MVB (fins uncanted, x~.ithout tabs) from TER

station No. 2 at Mach numbers 1.00. 1.02, and 1.04 are presented in Fig. 50. The wind

tunnel trajectory data show that the motion of the MVB is only slightly sensitive to

Mach number variations. The flight test trajectory data agreed with wind tunnel trajectory data when compared on the basis of displacements (Fig. 50b).

The photographic sequences of trajectory data for the MVB released from the TER No. 1 and 2 stations at Mach number i.02 are shown in Fig. 51.

4.6 DYNAMIC STABILITY DATA

The variation in _-pitch-damping--- _._ (Cmq_ + Cm.,;) coefficient with antic_ of attack is shown in Fig. 5"2-for the 0.075-scale model of the MVB with and without tabs. Presented

are the pitch-damping data for Mach numbers 0.50. 0.70, 0.90, and 1.10. Generally, the

21

AEDC-TR-78-4

pitch-damping coefficient increased in magnitude with Mach number for angles of attack

near zero. The effects of canting the MVB fins and adding fin tabs on the pitch damping

were not appreciable for angles of attack near zero. Conditions of pitch-damping

instability occurred at higher angles of attack at Mach numbe~ 0.50, 0.70, and 1.10 with

and without tabs. Figure 52b shows one case of instability in pitch damping for an angle

of attack of 10 deg at Mach number 1.10 for the MVB with all fins canted -12 deg.

Values of pitch-damping coefficient predicted by the method of Marshall and Summers

(Ref. 7) show reasonable agreement with the experimental data for all Mach numbers.

The predicted values were calculated on the assumption that the pitch-damping

coefficients are not highly sensitive to Mach number or angle-of-attack variations. Average

values of the pitch-damping coefficients for angles of attack between -+20 deg were used

as constant inputs for the computation of the wind tunnel trajectories.

5.0 SUMMARY OF RESULTS

Dynamic stability, static stability and captive trajectory wind tunnel data. along with

flight test trajectory data, were obtained on the MVB with and without fins canted, and

with and without tabs, at Mach numbers 0.50 to 1.10. The wind tunnel trajectory data

were obtained for release from all TER and MER stations on the A-7D and F-4C aircraft.

Flight test data were obtained only with the F-4C aircraft. Based on the test results, the

following comments can be made:

. Flight test data indicated that the use of a two-tail-fin cant is not a

feasible technique for alleviating the excessive pitch down of large

diameter stores wh.eja releas___ ed_ from TER station No.._l at Mach number 0.90.

. Comparisons of wind tunnel trajectory data with flight test trajectory data

for the MVB with and without fins canted and without fin tabs showed

generally good agreement.

. The wind tunnel and flight test trajectories for the MVB with canted fins

and tabs, from TER station No. 1, at Mach number 0.90, could only be

made to agree when using constrained motion in the wind tunnel data,

simulating contact and restraint between the fins of the released store and the adjacent stores on the TER.

. The wind tunnel trajectory test data showed that the MVB released at

Math number 1.10 from TER station No. I with fins canted and with fin

tabs showed no improvement on release as compared to the uncanted fins.

22

AE DC-TR-78-4

. The wind tunnel trajectory test data indicated the MVB with canted and uncanted fins and with fin tabs could be separated from TER station No. 2 :md 3 tbr Math numbers 0.50 to 1.10.

REFERENCES

1. Holmberg, John L. "Tradeoffs Among Weapon "Aerodynamic Stability, Trajectory Perturbations, and F-4 Aircr~lft Performance." AFATL-TR-73-47, February 1973.

2 . Test Facilities Handbook (Tenth Edition). "Propulsion Wind Tunnel Facility, Vol. 4." Arnold Engineering Development Center, May 1974.

3. Tipping, Derrick, et al. "Computer-Aided Missile Synthesis (CAMS)." OR 12,034, June 1972.

4. Gomillion, G. R. "Aerodynamic Load Characteristics of Six 0.05-Scale Stores in the Flow Field of an F-4C Aircraft at Mach Numbers 0.5 to 1.1" AEDC-TR-76-45 (ADA029144), August 19"~6.

5. Allee, E. G.. Jr. "Static Stability and Separation Characteristics of the CBU-24 Dispenser Fitted with Various-Tail-Fin Configurations at Mach Numbers from 0.5 to 1.10." AEDC-TR-70-37 (AD865412), February 1970.

6. Kratzert, Keith A. "lmpro~.ed Cluster Munition Evaluation." ADTC-TR-76-61, August 1976.

. Marshall, J. C. and Sutnmers, W. E. "An Analysis of the Relative hnportance of Parameters Required for the Simulation of Store Separation Trajectories." Aircraft/Stores Compatibility Symposium Proceedings, Dayton, Ohio, September 197 !, AFFDL-TR-72-67.

23

I

I I I ~ONT'OLLEll i

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THESE COMPONENTS LOCATED INSIDE TUNNEL

_ J STOLE SEPARATION I I "1 DRIVE ISYSTEM J

|

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. ! °°,,^**° N.UL,,-o. ,~, U o,o,,~. J ANALOG l CONVEITER II ~'-I~P"I CONTROLLER I~MMUTAToICONVERTEIS S

t~

Figure 1. Typical store separation installation and a block diagram of the computer control loop.

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TYPICAL PERFORATED WALL CROSS SECTION DIMENSIONS AND

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/ --STORE F cTS STING SUPPORT

" ~ / - ' - " - / I F -4 MODEL , ' -~ , ~ ~ - -~ t

!

I STA. STA. 90.1 150.0

t m

a. F-4C Figure 2. Tunnel 4T test section showing aircraft model locations.

o.-- - - 0 . 5 0 0 DIAM ~ - - AIRSTREAM SURFACE

TYPICAL PERFORATED WALL CROSS SECTION DIMENSIONS AND TUNNEL

STATIONS IN INCHES

t ' .J .,,,j

f SOLID AREAS F PERFORATED WALLS ( IO I[, MAXIMUM OPEN AREA)

i A-TD ~ - S T O R E MODEL

MODEL

EXPANSION REGION

STA. STA. STA. STA. 0 .0 36 .0 90. 52 150.0

b. A-7D Figure 2. Concluded.

m o cJ

.,~.~t~/------ 0.500 DIAM ~ - - AIRSTREAM SURFACE

" ' t - - " ~ " /

TYPICAL PERFORATED WALL CROSS SECTION DIMENSIONS AND TUNNEL

STATIONS IN INCHES

m 0

CO

t ~ Oo

ID AREAS /

EXPANSION REGION

STA. STA. STA. 0.0 36.0 106. I

PERFORATED WALLS ( I0 % MAXIMUM OPEN AREA)

STA. 150.0

Figure 3. Tunnel test section and installation details of the 0.25~cale MVB model.

I

"=---1

ORIVE MOTOR ~,NGLE OF ATTACK

SEISMIC PLATE

r/s1

q

,ib:

TUNNEL (L "~

i lo

I ,

=___[

! N ,,

~, . - - I~OOIEL STING

.~ ,~TYPICAL MOOEL

_ _ _ i ~ ~ , - -

~ I N E R T I A DISC ~MAX " :4"

f l o l b Mof * 200 racSion

--COCKING MECHANISM FREQUENCY ,n IO-30 hz L AIR GYI.INOER

l ~ . ~ C R O S S FLEXURES

/ ~ J--CLAMP RING ~L~ ~ A I R CYLINOER

Figure 4. Tunnel 1T dynamic damping rig showing installation of 0.075-scale MVB.

m O o -11 4:O

AEDC-TR -78-4

- - ~ WL 0 . 0 0

BL- i 1.560

BL. 4.075

F S - I.&B5 FSO,O00

|TATIQ#JS IN INCNE8

BL 4.07~ ~L INBOARD

PYLON

BL 6 . 6 2 6 - re. OUTBOARO

PYLON

FS 2 ~ 9 4 2

BL 11.660

a. F-4C Figure 5. Aircraft models.

30

AEDC-TR-78-4

.EL (1000

,o \ ,~,Lo, sT, 2 , , L . , . o _ ~ . : _ ~ _ \

,P,LoN sTA. ,

a L - I I 6 J 9 " ~ I

DmEI IS~NS IN JNChE9

FS 6 795 z \ I i ,

20.099 22 263 35 eO0 20.553


31

W L O.O(Ref.)

3 °

E

ND 3 0 - IN. SUSPENSION POINT NO 14- IN. SUSPENSION POINT

~ - - - - - . - - F -: G v ~. B -

D f

C

B

C O E F

G

INBOARD CENTER OUTBOARD

1 . 0 3 0 1 . 0 3 0 0 . 5 1 5

4 . 5 8 0 4 . 8 5 0 4 . 4 3 7 1 . 9 0 5 1 . 6 3 0

0 . 5 7 5 0 . 5 7 5 0 . 9 5 0 0 . 9 5 0 1 . 3 5 0 1 . 3 5 0

2 . 0 0 8 0 . 5 1 3 0 . 7 5 0 1 . 1 5 0

DIMENSIONS IN INCHES

3> m O

-e

CO J~

a. A-7D Figure 6. Details of the aircraft pylons.

A E DC-T R -78-4

WING CHORI

FS I L55 L_ ~ --1.91

F I .827- , (

~.~' Q O ~ -

. 8 7 9 - -

1,279

5.426

35.00 R

WO 14-1N. SUSPENSION POINT

NO 3 0 - I N . SUSPENSION POINT

lit. 4 . 0 7 5

_ ~ .250 o


b. F-4C Figure 6. Concluded.

33

3.341 2 516

- - - 0.916 -J

__oo+ !1

t WD 14-IN. S U S P E N S I O N ~ ~ I POINTS ,

• - h316 I J'T L - - - - A

- - - - FWD 3 0 " IN. SUSPENSION POINT


0"303 1

0.713 [iiIo SECTION A - A

a. F4C Figure 7. Details and dimensions of the aircraft TER models.

m 0 :4 -n : j co

U,)

0.920

0.800

f

3.335 2. 550

- J

w

~wo,..,~o,~.~,o,-~ 1.320

I

J

f l


FWD 30-IN, SUSPENSION POINT

SECTION A-A

o.!2


r n cJ

2]

00

O~

i 6.62:.791 _-

5.173 5.76 ~ . ~ _1

28-9° %

×i _r_ / 5o

; DIMENSIONS IN INCHES

~> m cJ

: ! " n

k

Figure 8. Details and dimensions of the A-7D MER model.

-,.,1

FS 10.652

WL

@

0.500

t

FS 16 0 5 0

V _ l

\

12.000

BODY CONTOUR,TYPICAL BOTH ENOS

BL 6625

STATION BODY DIAM

0 0 0 0 ' -0 0 0 0 0 0 2 5 0 I 0 0 0 .050 0 144 0 150 0 2 5 0 O 250 0 3 4 0 0 500 0 496 0 750 0 622 I 000 0 ?24 1 250 0 6 1 2 I 500 0 050 I ?5O 0 958 2 0 0 0 I 016 2 250 I 0 7 0

STATION

Z 500 l 750 3 000 $ 250' 3 5O0 3 750 4 0 0 0 4ZSO 4 5 0 0 4 7 5 0 5 000 6 0 0 0

BODY DIAM

i . i i 6 1 156 I 190 1210 I 24Z I 2bO 1274 1286 I 294 1296 I 300 I 300

3 1 t f

- |

FUSELAGE STATIONS AND DIMENSIONS IN INCHES

Figure 9. Details and dimensions of the F-4C outboard 370<jal fuel tank model.

7> m 0 c)

"n

O0

UJ O0

~ . _ X c g . . ~ ~-.-SEE NOTE A SUSPENSION LUGS ,~S"HER., / -OGOO #v-SEE NO~E B . /

o ~ \ o2.~- S"HERR I°r~-'~'t ~ ~0400DIAM " ~ J- / OlAM ~AM . . V ~ - - / 4s" 3 C T ~

p_,.oo w.-,-.ou-r-r.,,s 4573. - i

' WITHOUT TABS

SUSPENSION LUGS

~ / SEE FIN a .._~~AB DETAIL

WITH TABS

N

WITH TABS

o BBG ~ O , 5 0 ~ I

!

oo.o -II-o.olo t j i - r

I . ~ ° ~,oy

FIN AND TAB DETAIL

NOTES A HINGE LINE AT 8" FROM BASE OF FIN B HINGE LINE AT 5" FROM BASE OF FIN


LUGS

m 0

-n

G0

Figure 10. Details and dimensions of the O.05~cale M V B model.

ii ~ ~ ~'~i~i I~'~

e e

v Q t .

P ~JlP ~p ~p IP IP !P ~~P ~ ,qDe ' ~ P ~ ~I~,~~

,~,.,9 ~tj, ~,D ' ~ <9 ,.9 ~ ~ ~ e * * ~ - ~ _ ~ l

i/ P.~'JP JIP .~9 9 9 ~ o B ~*IA E D C

3080-76

Figure 11. Tunnel 4T installation photograph of FJ, C aircraft, M_V_B_~and CTg.

~> m

c~

O0 j~

m

o

:D

0o

4~ O

J- 22 828

2 I .O00

Xcg " ~

!

L - 1 3 0 0 D I ~

I. 170 DIAN

• z-----~-7750

° ' " "

LSEE FIN a TAB 0ETAIL ORWG~

~ SUSPENSION LUGS

OIMENSIONS IN INCHES

a. Details and dimensions of body and fins Figure 12. Details and dimensions of the 0.25~cale MVB model.

. L

30" 0062

~.__.~ 2 2,~0 . ~ _ l . 1 ~ - ~ 2 250 "~-~'-~ -~1~ m-C062 ---- I 250 "-" ] ..P-12,50"--~

FIN DETAIL WITH GAP FIN DETAIL WITH NO GAP

_ ~ - I 250 ~ U S P E N S I O N LUGS

CANTED FIN CETAIL

DIMENSIONS IN iNCHES

~ - ~ - 0 344 -0214

400

39O0

_ ~,'l J

~v S °

m . "iV jE , , , ~ . - 0 3 4 4 0 050

TYP J .__ _ _ _

450 ~ " ~ T ~L; , , -!

. I i I ; 678 J

, -~ ~___

I

i I

TYPICAt' TAB DETAIL

b. Details and dimensions of fins Figure 12. Concluded.

TYP

m o c)

=0

O0

/ o

D

D ~b

D

D D

b U

u b b |

~) L) D i ) ~ D D

D D L) I~ D D 0 m ~D D D D B D ~ D D D D D j

D ~ ~ ~ D D D i ) D ~ • D i ) L) D

D i ) ~ D D D D D ,D D ~ ~ D D L) D m D

I) D ~ I D D D D D D U D D D D ~D D D ~j) B

M D D D ~ D D ~D tD D ~ D D D D D D

I~ D D

0 0 ~ * J - -

~P

• D ~JLD D D D D D D D ~I) D

• D D D I~ O ~ D D D ~ fl~

ID D D D D

~J) D . D D D

D D ID ~ IP D ! )

D ~ D B

D ~ O IP Q D D O Q 4 )

D D 0

~ 0 D

LD LD t P ~ D

~D D •

LL m ID

J

D

~ .

W ~ ~ Dqp D "

~ ~ R eO

9 0

D a w

04)

t 0

'LP A EDC P

i~ 5291-75 • i

0

I l l

(~

-11

co

Figure 13. Tunnel 4T installttion photograph of 0.25-scale MVB model.

J~

Figure 14. Tunnel 1T installation photograph of O.075-scale MVB model with interchangeable tails.

m 0

:0

j~

AEDC-TR-78-4

.... i'/~:~ : . , , ~ i ~ ' ~ ~. : ' ~ : = : ~ :..: ":~

a. Side view .

b. Front view Figure 15. Installation photograph of fuIl~cale MVB on

TER and F4C aircraft.

44

i !

u t

\

c. A f t view Figure 15. Concluded.

> i l l O

::0

J~

UPSTREAM

UPSTREAM

A E DC-T R-78-4

M E R

i - . ~ S U S PENSION LUGS

See Note

I TER

NOTE: The square indicates the orientation of the suspension lugs

TYPE ROLL RACK STATION ORIENTATION, dog

MER

qP

TER

I

2

3 4

5

6

I

2

3

0

0

4 5 45

- 4 5

- 4 5

0

45

- 4 5

Figure 16. MER and TER store stations and orientations.

46

A E DC-TR -78-4

SYM M= 81 8 2 8 3 8 4 FUZE TABS FIN GAP O 0 . 5 0 O O O NONE NONE NONE I"1 CAMS PREOICTED (Ref. 3)

'~ ~~ftt:t il it I:t !iI tiil~ it t]! ~It [!~tt ,l~t~t:t:~l:! ti!i:il t!i!~ ii!ii!:H!

: : : . ; - 4 -4 " ¢ ~

I t ~ .

" ! r I . ! , f l " - t t

; r ÷ T , ~ ' , H 4 ~ i -i~ *-~. '~]l l i ' [ -; -q0 -30 -20 -10 0 1"0-'" 20 30 q0

¢l l

.ILh-q-I I:~.-~l.t-l-~-I~!~.I ~--- -H+I I ~-i-o.. ~m_~ '-~-~--,-~-'+44-.'

~. 4-4.-,- -- ,,.-..- - ' I-~ ~--' ~- ~~'~I~ ~~ ~IN ~i~l~i~!~.~ ~ ~: o ,~l~Ill~l~,~l~II~!l

- I " ~L.L- '- I I I I I ' , " " ' " ~ ' u ~ + h LH-H+~ , , , , , , I,-H ."rr.lfl:i:I::l CN ~ l l : [ , : ; tl!!i,~,,,],,,,,,,,~-,--,;,,,,,,::~,~--~,

.l I - : I I I I I I I ~ | [ ! " . i I I I I I I I ! I ! I-TT.'T-I-~I

[ - - L I I I I I I I I I ' " ; i , iI'-r+:;iiil,l

i j L I I llllI Ill "- t I I I! IIIIIIII ii i i i i i i I I I I,! I I LZI ; I I I I I I I - ,,,,:,,,,,,,~ :-,~,,,,,, , i illlllll :,

=3 llllili'i I- ;~ !IIIIIIII I ~I lllll Ill I

~ , - ~ - ~ ' t - ' I I ' , , , , , " , , - ~ t -Iq-H-H--H-H ' " I ! [ ] I I IIIII=II

, , .,,,,,,,.J._LLLLLLU-~..,.-;-~.~ II I I I ' "

3 2 1 0 -1 -2 -3 -l~ C a"

a. M® = 0.50 Figure 17. Comparison of wind tunnel 0.25-scale MVB static

stability data with predicted data of CAMS.

4?

A E D C - T R - 7 8 - 4

SYM Moo 81 ~ 2 8 3 ~ 4 F U Z E T A B S F iN GAP

0 0 . 7 0 0 0 0 N O N E NONE N O N E r ' t CAMS P R E D I C T E D (Re f , 3 |

CN

'i t!iiittl - ql-

| .

0

.,!~t~4:i, -qo -30 -20

! - ; l i l i ~ d • : ', I i , l ~ , # T • -~.l,r'i'd ,,~,,~- !

:: ii[il:~t " !, il ' :' ' i i '

I--1 : it "'!, , t '+~

t * ! ' ' ~ ~ ' ' +'~ ; :~+

li "" " 1 - * $ '*$

-10 0

i1! t t!i. !~.. #! ~! iil!i~t,,.

. ~ ' T t *~

I~I I ; i ; 0 + .*,++

t t ~ ! l - l • ,-:i_! ti !i.;i

: : K-; . - * t - , + o ~ *-f.. ~* I

I0 20 3O qO ~$

|

0 CN

-1

-2

I l l l i l l l ! Y / .

t l I I l J I i i i 1 - [ q q q r l l i i ~ _ ; L I i i i [ i '_ ! . I-] | I I I ; I I ~ ; l I I ,~, : . , . ,, ,, ,, ,,,

.~ H-H+t+HrH-

L~

t-!

; J

g,

t ,_,...,.-+

"%1

tt.-~?, lit~-1

H-~; |-,--~ i i Fl-'..-:. i-.,.4-~" • - . . . . I-~4-'I-1" t t - + ' ~ Pl ~4~ -o ~.~. ~ . - f - f . - . ~ - f

i -~ -~~t - l -~

~!1!~-i t:_Itti:l:rii! r ~ + i - H - t ~ - d - : t .-i-H-

--t-H-i-- ¢~ ~

L~-H4*-H-H+I-.%~T- ~

I ~ L I _ I _ L ! : [ . 1 i i i i i • I I 1 T 1 7 - 1 " ] - - ; I I I ] I 1 L . I I

0 -1 -:~ -3 Cm

-q

b. M= = 0.70 Figure 17. Cont inued.

48

A E DC-TR-78-4

SYM M= 81 8 2 8:3 ~4 FUZE TABS FIN GAP

0 0.9 0 0 0 0 NONE NONE NONE {3 CAMS PREOICTED(Ref. 3)

C. 0

- !

- 2

0 C.

'l~i!:ffttt ':~¢ N!

lt~!ifl!l~itil, r:~ - 3 . . . . - ' ' - ' - " "

I~I/~r-i.{t ! -.t..t. -,.- ,,

-~i I t . - t1 f - t f+~- t ~ - I I0 - 3 0 - 2 0

-1

~ . " ~ - 1 " 1 | I 1 i I I

' ~tltf~t:!

-VVVrll I [ [ l I

'NNt~

-i!III-! "t!!t! i " -

i

~illii. r., ' '

i!t-i,. i. !i~

i-: ! i ' t ; . ; .

t ~ i , , , : .~". :.:.;-,.

- 1 0

l-,.-f-° .-;1-4 • :., .-f ~-+1"!'

r t-l-'l"T, -~

, , i l l :

l:-Hii~-I

-H-t-~ 1

iilit! ii~l!lili?f! ~!iit ~l!ii!iiii

! • 4 f t

, . i I. ~! ' !

'i i ' ' ~ ' ' ; i ) e , 4 . I . . . . . . .

. i.;., , i . . . .

! , , i,[_. i : - t , .~ - , .

I ~' :: .... ; , I ~ ! @-4' I' I - I 4

0 0 20 30 qO ~$

Nt!N

' / ' :

t--H-~, t ..L~,

t ~ ' - " - h - I + t

I l l l l l l l l i I 1 1 1 ] I I I I I

l l [ l l l ! ! l i

0 - ! C,

• . • 1

. . . . . ~ - ~

H-! ~ ~.~~ l i LL~_LtJ .LLLLJ

~ r ~ + ~ r r ~ r m

I I • l i i l l l ', i~ ~-i-iiiill ! ',:

- 2 - 3 -~

c. M . = 0 . 9 0 F igure 17. C o n t i n u e d .

49

AE DC-TR-78-4

C .

C .

- !

- 2

- 3

SYM M m ~t 8 2 ~5 84 FUZE TABS FIN OAP O I . I 0 0 O O NONE NONE NONE D CAMS PREDICTED (Ref, 3)

2 t .iI~ It.

l~II+l+lllll-! iI+~+~I I i~llii,,,-,. ' "II!lll 'liii '~ ii +i iii - . ~ ' . ! ~ ' :

o ~!~+ti :'t!! i ~!! ,I .

++~+~!,+]li i+I -I - il- ! } ! i I l l i t l

~]~TIT + ' " ' + . . . . .

tiil~ +I, I-~ t - , I -~ . . . . l i , , , , , , , + - + + 6 + I t + , + ~ ' + ' + + " l + t ~ +-+ . ~

~-+-~-+ • I ~ . + + ' ' I * +

i+"-i-I-++ . . . . ++I " * ' t * i o ; l ' ' ' . . . . 3+ , ' . . . . : ' + + + | . . + . . . . : - + + ; 6 +

I+-~4.+ i + , +, , . ++ i i i i i . . i i

- ~0 - 3 0 - 2 0 - 1 0 0

|

0

- !

- 2

- 3

~ S

. . . . : I

i ,4--4-,i, - - -

I--'4"'4"'4' I - -# - -P ' t I I I I

I I P !

[ I I I I I 1 I I I I I I l l i l i l ' l t I I I l i l t I I I I I l l l !

ILl ~-H-++-i- L l l i l l 3 1 1 1 [~-I-H+~--I--I-I-I~

J . l l I i I I I I I I I I . L

Li!

i ;

e 4 , ! .

. . i I

i flit.,, .. 4 * e * ~

i i E

f,-+ •

tO 20 30 I~0

i ; - - ,

!-~ ~2~19i +.'+~ . . . .

. - . 4 - 4 .

i-itINl!I~:~ " • ,i,-,i,

,i,- ,i

-,l- ,o,,,

I..L"IE,,LLLL,J.,.LL,LLt i ] I ] i i i i i [ a Ii~ t.I ] ] I ! t LL,L.LJ.J_LLLI IIIII , I , , , F H + H - H ~ _ ~ I i i i i i i i i i i i i I IT'I-T'F'TT'I-I-I i I I I I I I I I I I I I I . L I I l . i i [ ] I i l i ] I i i I I i i i L U , J . J J J _ L L L J I I I I i t I t I 1 1 1 I i : ' ~ i 1 1 1 1 1 1 1

I I " ' I , ,+H-H-H-H-I+F~ t T, ,-F'~q-,, FFi I i i i [ I [ I I J - L L L L L i i I I I I I [ i [ I I I [ I | [ / ] I ] ; / / I I l I I I I [ I E l [ 1 1 1 1 1 [ 1 1 1 1 L ] 1 1 1 1 1 1 l l l l I ! ~ I I I I I 1 1 I I I / i I | l i l I [ ! 1 1

| ~ I I I I I 1 I I I I l i l [ l l I ! J j I . j . l I I I i i i i [ i I i I i t t I t i ! i I

I I I l l l I I ' [ l - t J : : L - I _ ~ h b : l : t , , , , , , , , , . - H + ÷ t i / 1 I I . [ J _ L L J _ . [ J _ L L L t i i t i i i i i L J I ~ ' | - r ' T - F T [ 1 t t / l i i i : i 1 i i i /

L 0 -1 - 2 - 3 -Li C.

d. M = 1 . 1 0 Figure 17. Concluded.

50

AE DC-TR-78-4

STN I% t I la % ltl FUZE lnD$ @ 0.5 0 0 O 0 NONE NONE [9 0 .5 0 0 0 0 NONE NONE A O.S 0 0 0 0 NONE TES @ 0.5 0 0 0 0 FHU-56 1ES

FIN ~ XNp NO F I NS - 60.69

YES 35.36 YES 46,75 TE5 45.80

2

0 C.

-!

-2

-3

_ l ~ l l

-qo

~t;tilt-iit ~itt !tt~!li ,ii , ti i!t!l,

.~:tli!t ;.;' l,,li, ,1~ ~ .~1tt~ -,-, 1!

I i t 1""t" . , Hi !~ - i !;

I*_~ _: i , I . i I ~ - - , 4- ! 1 t I

I~I It' till ~ I-r-l:~. i , i l -30 -20 -10 0

~ $

i~llli~' t! i,i, ,:' ::

! t ; li 1 , ~',i' ~: ! I"* " - *

ii!i , '

!!i.!11~, - " " - " I I I t "

'4 T -: ~ , . . ! " ,

0 20 30

tl :i

i ,

!

i'

I- i q o

£.

'lH':t~i~!!lii Y ' l l ! ; ] ~ ,

2-:-.'-'t.

- I '-1 ++-,-, [t 7 i - , -+ - , - - . . . . . . -~-~-~-~!~t.t-~ . - t - - P • ,

, , 4 t

,,-,I- ~ I,,.,,t - ~ - i + l - - i

- ' I I I I

I-i~ ........

-~-t • , - * ~ - f- ! [~!; I ~! i - i~t ; '~i i-+~, !1 b-l- II !tY~ !-t:i I t~t?17!!

. . . . 14-1:;.~:I-~ ~:

Hi-: x _ ± ; i -.---rrrti~-~l~d-i4q~ -7-'_~t:t--ETE~-r~; T-i-t~--r

I!N~tTKh!H~,b~ 1 0 - ! -2 -3

Cm -4

Figure 18. a. M = 0 .50

Effects of fuze, tabs, and fins on the 025-scale M V B static stability.

51

AE DC-TR-78-4

S'fH H. i m Ill is i~ FIJZE TRBS FIN GAP XNp Q 0.7 0 0 0 0 NONE NONE NO FINS -63.36 [] 0.7 0 0 0 0 NONE NONE YES 32.096 & 0,7 0 0 0 0 NONE YES YES 47, 36

0.7 0 0 0 0 FMU'r'~ lE$ YES 45.98

0 CN

-I

-2

-3

-4

' t:~:#.~t~-7-tt ~:~:~ ..... t l'ttttti- tti-~t :I~t i

ttt~l~f]-flt-_tt:t:t.H~ ~ ' = i 1 , : !:itt ~f!tl:l-~lt t~t -!t ti1~i ! t i '~- =~-' t::f!~ittt~t-i !i ! i I-! :I-t tt-!t t-ft~! ~.i:,tl

-i- '.- ' ]~. ' - - i : ! . i ,.1. , : . : , . : . . ' :

-40 -30 -20 -10 0 10 20 30 40

3

2

0 CN

-I

-2

-3

- 4 ' 4

=¢$

3 2 l O - ! -2 -3 -4 Cm

b. M= = 0.70 Figure 18. Cont inued.

52

A E D C - T R -7 8 -4

S~N

CN 0

-1

-2

-3

I% sz ~z ~s % FUZE TRBS FIN GRP XNp @ 0.9 0 0 0 0 NONE NONE NO FINS -28.72 m o.g 0 0 0 0 NONE NONE TES 35.04 & 019 0 O O 0 NONE YES TES 52,59 @ 0.9 0 0 0 0 FHU-56 YES YES 47.34

-qO -30 -20 -10

-:~ it t----t! -!~H tt .... !t!-!.~, .,

!iiii! ' -!-.. l~: -

ii+ i- . ;

!f~! .,- . . . . . !! .

ll~li i+IIL

; t

i~ti 10

er S

I-tl t~::l ~ t t-i!l ' i ~ ! .

, I

i 1 ! ,

]

lit !:! t tit ~ i i ~- t I ,

. i -+

- i - I "

I:ii~+ I + I ' i. ' -t'" [

20 30 qO

CN 0

- I

-2

-3

3 2

i~ ! l !~ ' ~+~ .. ~ , + , L i ! . ; . ! r ! ; - [ i: - ..,.++.- : !, ~..,+.._: ;- : ~::+'r ;-'-,+i i t ! +:~++,-t:, ~!!+ + i ; ' ' i . . . °'l+'i 7 k + i : ~

" ' - ' ,I~': .:! , , ; , ,.,:~ t!i-.+.._. , t-!l-t- r + i . ~ . . ;-t "

+ • i -~;-~ i :i .~i =-i-,-~ ' " ~ ..i~!it- I l l , ! ' 1 ! ' , d ,'-" 1 t I ' I - ; I " : T j . I I ; L i t , ! I I I ' t ; : l | ' i I ;

; i : J ; ' '

t +"I t |+~'i I - I ! 1 1 i t t " ' 1 1 I I 1 ~ 1 i ! ] / i

+ "+i!! !(i-~+I~" l ! 1 ! ! - i - l t I ~ ~ _ .

• i i , i + l l i ! i ; !-'i ~ - t t . 1 ~ - - .

, 0 - i -2 -3 -q C+

it f i i l - : -H , +:1.':!--~;.

• ] ' i / , " " , " l ' " T-,' . ' ~ T T ' r ' * T *.',* l

t ; t ' : : f " l I I I I ' I

' ~ ~-iT T ' r~ 1

1.1.?; - ;. t-t-+ :- I t ' ; i - ! ' 1"1 ' : - -~ •

! l-!-~ k!.-t-t. 1i-14 !:i-:l,-t

1:t!i-i:

c. M= = 0 . 9 0 Figure 18. Cont inued.

53

A E DC-TR-78-4

s'rN H,, 6 t ~ 6= ~ FUZE TRBS FIN C.,RP xNp 0 I . I 0 0 0 0 NONE NONE NO FINS - 54 .05 13 l . I 0 0 0 0 NONE NtJNE YES 3 1 . 3 6 & ] ,1 0 0 0 0 NONE 1ES YES 4 5 . 4 7 @ t , l 0 0 0 0 FMU-56 "fES 1E5 4 4 . 2 7

CN

CN

- !

-2

-3

-q

mmlt, t~lt~!i I Jlli!ill~i;' ! . . . . . . . . . . 1 ! I " ' " " ' " '

. - - : ! i ' '

~'-*" l!lil! ~ i~ I ';I '~ . . . * - ~ -¢ -~ ~ - I I t I . . . . . . . . . . " t ' ~! °°

!!tH~ ~ it i t i t1- 1 - ~t t .~ r . !i

t~l~!hit!ii !~'t i l l ~'* • - , - - - - - : - , - i ~ J i i 1~j

' t l ; t ! i ~ ' t ! i i i l l '-~ - . . - , : : - , i : , ! 4 - - ' l : : ~ -qo -30 -20 -10 0 !0 20 30 40

~ '$

~T-I~--I-'- iL!:-!:I : : IL, . I .-t-~-; ~ ~ , - . 4-,-~-~ ~ ~ ..... ~-~ ..T ~ ~,i. qp~-. t-~.-i,f ~ i . T ~-r. -~I-I- I- . ! f f l " - ! ~-i l . t ~ - ~ . ~ t - ~,-r:-, ~- , ,-. i :-c.#!

1 "1 " - - - I - 4 . 1 r , ~ ~ I - I , - , ~ , l iih , ~ - , ~ . - - , I~0~ i-t ; i'-I, I"-~'T " I I " ; i

. . . . . . . i:L~! ht~ !.1 ! i~ i I~.~14 t i-i i-it i-i ! i t ~ ~;--: I

- i~ ,~, TI i I-I ll-tat-l-I -,-~. flr-Hit _| f t - l i ! i ! 111 11 ! T r l 11-1 i , • : " I - r r Z r l

t ' I ' ' ' i l l "1"' i ; l ' l ' l - i - i " :-~--I-t ,"-~-: =1

f:!1:11:!! HI~ l;ti! t!fitt]tHiHi4#l ['. Hl i;!l-i !1:', !t<i l:!!i-:,i H!;~t~ttI ': t i tt:!-t;!tifl

t~ 3 2 I 0 -I -2 - 3 -q C~

d. M= = 1.10 Figure 18. Concluded.

54

A E D C - T R - 7 8 - 4

SrN I% ~t ~ t ) ~ FUZE TRBS F IN GAP

0 0 . S - 1 2 0 0 - 1 2 NONE NONE TES 0 . 5 - ] 2 0 0 - 1 2 NONE 1ES 1ES 0 . 5 - ) 2 0 0 - 1 2 FMU-56 ~ES YES

CN

!! !I = ' 1,~ ,.= : . I , " ' , ' ' I ' ' ' i l . . . . I ' , t ~

,-t, I-i t "~:j~;.i::l::::t!il;tii~il::! i i l . i i I i i I ; " | . ; i a ~ j i l ; ~ ; : l ~ i ~ . . ; - ;

[ t . - ~ t - E l i ! : = ] , ' . ! . : ; ! . . . . : l : : ~ ; l i , . . . l - . . ; :-t.. [-! . , ~ . ; ' ~ , I . ' , ' : I . . . . I • • t L,J"~- ' ' I . . . .

" i t ' ' ! ' . I ~ ! I ~ ! : I : ' / - ' 4 ~ ; i i I ' ' : ; I

[ l

: ' . .

i 1 .... 1 .... ;~ , , , ; : . . . . . . . . . . . . . i~!! :;: ::~: : : : : : : ~ . . . . . . . . . : ~ : : ,~: : i : : " ! ' ~ ' ~ " ' - " : . . . . . .

o = I ly l [ I | ' • ~ • , , . . , . . ! ° . . , o ° . , . . . , , . o .

" , ' l . . ~ , . : . ; ; . . . . . . . . . . . . . .

I l l ; , : . . ' : : : . . . . . . . . . . . . . . . . .

- ' :::::::::::::~'T::::::::::::::::::::::: • * t : : I " : ~ . . . . . . . . . . : . . . . . . . . ] . . . . . . . . . l , " ~ ' , , . : l . . . . . I . ,

- 2 : : i ; . : : ~ " " I . . . . . . . . . . . . . . . . . . . . . . . . . ~ . ~ . ~ . ~ , , . . , , . . . . a . , • • * • • • - ~ . * • • ~ , , • •

, . ~ . I . . ' , 1 o . , . , , , . o . , . , o , . . * , . . , . o .

, ; . . . . . 1 . . . . . . . . . I . . . . I . . . . I . . . . 1 . . . .

t t • ! iiiiltill ~ ~ . . , . . , o , , , . . , . . ° ° o

. . . . I : : ' : : : : : : : : : I : : : : : : : :

-~I0 -30 -20 -10 0 10 20 30 qO ¢($

Cw

0

- 1

- 2

- 3

- q

3 I t I I : ; , . . . . . . . . . . i . . . . . . . . . :,~ . . . . . . . . . . .

Z ] ; . . . . . T ' ! I I : ' : I ] : : : . T T I . . . . . . . . . . . . . . . . I T " i i ~ i I . I i . I . . . . ! i . I I . i i l I - I I I I I - I I - - - I I I - I •

: . . ; .~ . . . . : . . . . :

~ . . . . 4 . =, • . ~ ' . ; t ; : : I i . . . . . . : . . . . . . ~: ! - : : : i z ; : 4 : ~ : I : ; : : t ; ; ~ : I ; : : : 1 ~ : : ; . . . . :1 ".,," : ' ' 1 ' ' : = . t " : !~ i . . . .

[ J . : ; ~ : ~ ; . ~ . . . . . . .-- i- ; : : I . ; - : : ,~ : ~ , t I ! t - , ...... i ! i * , • " , - ' * " - I • " - " . . . . . . . . . " ' " . . . . . . , I = = . . l : . . . . ; I . . . . ; . . . . . .

i ' " ; ' ~ . . . . . . : " : " ' " ' " " . . . . . : . . . . : ,.; ~ i . . . . . . . . . . . . . . . , t - :

. . . . : , . . . . , . . . . , . . . . , . , ; . . . . . . . ~. . ; . ; : ' ' : ; ' . . . . ; i . . . . . . . ~ ,L . . . . + . [ . . : . 1 . . . ' T -

i ! . - . , : ! - i i ~ ' : " ~ ' ' , - ! . - . - ; - ! r ~ - : . . - - ~ - " -

, ,I ' ' . , - I . . . . . . . . . . . . ? ' I " " ' • I , I ; . . . - , , . , I . . : . I . . . . . .

LI 3 2 0 - ] - 2 - 3 -LI

a . M = = 0 . 5 0

F i g u r e 1 9 . E f f e c t s o f f u z e a n d t a b s o n t h e M V B s t a t i c

s t a b i l i t y , f i n s c a n t e d .

5 5

AEDC-TR-78-4

SYM N,. 51 k,~ 5~m Ira, a FUZE TRBS FIN GAP 13 0 . 7 - 1 2 0 0 -12 NONE NONE YES 0 0.7 -12 0 0 -12 FMU-56 fES XES

CN

C N

3 ;i; ..... : ............. Z ............. o , , o m . i o , m , i , i i , . i [ i . . i J ,B~m-- ,i ''I-

:::::::::::::::::::::::::::::::::::: ............................. :ii[ii! . * , l l l l ~ m l e a , m ~ e a l m l . , l l I . . . .

: : : : : : : : : : : : : : : : : : : : : : : : : : : . ~ 1 ~ - i ~ ' - . . . . . . i : : : J~ i i i i i I i i i I i i i . . . . . . I I ~ / 1 1 . . . . . . .

I i i i I i I i I i I i i I i i i i I I I ~ : : . . . . . . . .

0 . : . . . : : . . . . . . . f ~ . . . :

: : : : : : : : : : : " ~ : : : 1 : : : : : : : : : : : ' : : : :

! i i l i i V i t i l i i i i t i i i i -2 ::::::::.~:::::::::::::::::::::::::::::

: : : : : : : : : : : : ' : : : : : : : : : : : : : : : : : : : : : : : : : : - 3 : -

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . !!i:!l:!!: • t o . m l , o , t . . . . t l , o , m , , , , e , , o o , l o 4 . . . .

, . o - i , , o o ~ . . . . l , , o o | , . , . p , , . o

-q0 -30 -20 -10 0 l0 20 30 ~0 ~ S

. b . • ~ . . . . 0 . . . . i . . . . i • • • . | • • o , i • o • • w . . . .

. . . . i , . 4 e l . . . . i . . . . I m . o . l e e o e l e e * o I . . . .

. j I . I . e . . I . . . . I . . . . I . . . . I . . . . I e • . . I • e • e

, i

iiiilii:i ii iiiil:iiiliil)llii'i- 0 .

. . . . . . . : . . . . : . : ; . . . . . : , - .

-1 ! . . . . . . . . . . . . . . 2 2 ; . 2 - : ; . i . 2 : : ~ , . . : 2

-2 . . . . : . . . . N . . . . . . . . . . . . . . . : . . . . . . . . . . . . . . . . . . : ' ' t ' ' ' 1 . . . . I I ' ' ' l ' ' ' ' l ' ' I . . . . . . . . i , l l l I l l i l l I I I l l l l l , l l l l l l l l l . . . . ~ . ~ l . I

n l I I I I I n I e l l l l I I ' ' ~ 1 ° o ' | ° I ' ' | ' ° ' ° °

I i I I I . . . . I I I I I I I I | I 0 " | " " I - -T | ~ ° I I

" " 1 . . . . . . . : ' 1 [ ! : : 1 : : : ' : ; ' ; : : I : : : • ' ' " ° ~ ' . , a

, . . , I . . . . I . . . . I ° ° ' ' 1 . . . . I ' ' ' ° I T ' ' ~ ' t " ' ' '

-H 3 2 0 -1 -2 -3 -~

C~

b. M = 0.70 F i g u r e 19. Continued.

56

AE DC-TR-78-4

STH II. ~i ~z ~ % FUZE TRBS FIN GRP H,L. (3 0 . 9 - 1 2 0 0 -12 NONE NONE YES 5 A 0.9 -12 0 0 -12 NONE YES YES 5 0 0.9 -12 0 0 -12 FHU-56 YES YES S E) 0.9 -12 0 0 -12 FMU-56 YE'S YES 8

C,

I ; i; i i ! i l i ! l ! l : ! ! ! l : ! ! : " ~ i ~ : : ' i i 0 1 i ~ ~i~ : . ' : ~ : i : : ~ : i l i I H i i ! i : ° 2 i l i ' ' ~

' ~ ~ ' *i!! !iii~ i!!J!~ i ! ; * . t . - ' t 1 ' ; " ! : [ : [ 1 : : : : 1 i - . ' ; I ' " , T . . . . . . . . . .

. l - i : : [ : : : ' : i I

° . . . . 1 l:i <]il]i:!liii!ti]:: : ~ : i : ;~ . . . . . . . . .

i i:~,-:::: ::: ~! : ! T ! : : I ~ " : ~ / . . . . . . . . . . . . . . . . . . .

. ~ ; , ; , 1 ~ , ~1 ! I t I t , . . . . . . . . . . . . . . . . . . . . . . . . t i | .6 . , , . . o 0 , , . . . . ° , . . . . . . . . , t . ! . . . . . . . . . . . . . . . . . . . . . . . -3 : . : ~ . . . . . . . . . . . . . . . . . . . . . . . . . . . .

-~0 -30 -20 - IO 0 !0 20 30 qO ~S

2 " i " ° ° i ! i i i i

0

CN

_ ! , , . ! . . . .

- ~ ~

Lt 3 2 ! 0 -1 -2 -3 -4 C,

c. M = 0 .90 Figure 19. Cont inued.

$7

AEDC-TR-78 -4

STH I~ sn sa ~] % FUZE TABS FIN GAP 1,1 - I E 0 0 -12 NONE NONE TE5

& I,I -12 0 0 -12 NONE TES TE5 @ I . I - I ~ 0 0 -12 FHU-56 TE$ TE5

0 CN

- I

- 3

Coo

- ~ ! , . t

IIi, I Ii :-i . ]

" " : ! I i

. ' 4 1 , ° . ,

l i ; i ~i" : i i : <

1 ' I " ' 1 "l-t .1. ,-1 I . ; , . , ,

I-:-2- ,

t ; : -

o r ;

l i ,

!

L I ,

i , | ,

!

!

-qo -30 -20 -10 0 ! ~ S

4- n . .

t - i . - ~ "T ~ - e - ! ~4-~ ,

t '. ,~ 1_ • ' ~ J " t ' - I "1 ° I - i - "

-- l II; t l u : i -,-1 L ~

V'. I t "

12.-! . - : t t - , . " ' I 1 "~ i i ; ~ i - ~ ! _~:tl !ii!

- • ~r~l -Lt 14 3

I t iJ = t i ! . o i

• w ,

--i--I

t t ~ t • ,o

; i ; i ~

I-1 1-I- 1 - ' , w, J

4 I , - ' 1 - I

-L ~-I

-1

ti: =!!il , i ~ ,

- r T't

0

! t"* ' a l!l I!

• t I o •

~t ~ ii~ i l l , l . t

, | • , , , e

i , , ° o

. ( o ,

12 i : : 1 . , . °

o o ° ° i B , ° ,

1 , , , e

, . o

, . . o

• , , ,

, P , T

° , • •

i ° .-, o

0 20 30 ~0

"

• ° . - r ° - - t • • . , , - . .

. . . ° . . .

t • t - - -

i t " " ; . . . . . i . . . . .

- - i - - ;-~-~- ~ • - ~ • . - . - .

: : ! . ; ;.

• i t - - •

, n - i • -

, L.i -- , , : I-~ -

11!t ; ' i - i " I . '--, ~ rT-t- t ~-i-i '

-1 -2 -3 -I1 Cm

d. M = 1 . 1 0 Figure 19. Concluded.

5 8

A E D C -T R -7 8 - 4

STH I~ 6: 6 a 63 ~ FUZE fgBS FIN £~P SCALE 0 .5 -12 0 0 -12 FHU-S6 NONE TE5 0 . 2 5

0 0 . 5 - 1 2 0 0 -12 NONE NONE NONE 0 0 5

" " : : ; i

" ' t , ~ , . , T.i. ~ ,

I" - - i ~ , j

I " ! , . ; , , . :L" I ~ : 1 ! - I t w •

: I " , ,

~i, ~1 ! ~ ~ C N t l , !! :

- 1 , . , . : i i

':. t .* - - . . . . . ' . 1 ' " • e - . ,I t - t ' • •

!!t o

-3 ~ . . . . . . .

i :

, T i • °

-LI . r i ' '

-q0 -30 -20 -10 0 10 20 30 q0 m S

C.

" ,h

• I-;- i

~ ,

-3

g

i i ; 1 1 | l

i

2 1 0 -1 -2 -3 -q Cm

a. M= = 0.50 Figure 20. Effects of model scale on the static stability

of the MVB, fins canted.

59

A E DC-TR -78-4

51M M. I~ I la ~j b~ FUZE TRB$ FIN GRP H.L. SCALE

& 0.7 -12 0 0 -12 FMU-56 NONE TE5 5 0.25 O 0.7 -12 0 0 - ]2 NONE NONE NONE 5 0 .05 Q 0.7 -12 O O -12 FMU-56NONE YES e O.O5

3

-q0 -30 -20 -10 0 l0 20 30 ~ ~ =$

3

i CN-I

'4 3 2 1 0 - I -2 -3 -LI C=

b. M= = 0.70 Figure 20. Continued.

60

A E D C - T R - 7 8 - 4

STH H= 5e *~ ~ '~ 0 . 9 - ] 2 0 0 @ 0 . 9 - ] 2 0 0 0 0 9 - 1 2 0 0

FUZE TAB5 FIN GRP H.L. SCALE -12 FHU-56 NONE TES 5 0 .25 -12 NONE NONE NONE 5 0 0 5 - 1 2 F M U - 5 6 N O N E Y E S 8 0 . 0 5

CN

C.

3

2

0

- !

-2

-3

-q

i ' i i - J i i ! ,

" t - . ;

t * i I _ 1 i -

i 't=

' ' i

+ Ii t : I ' ' ~ , - . , i ;~

'

iri i ; ' t T

+ : +,

, |

~ "

• °

f o

• o

t • • ,

o , •

• o

-q0 -30 -20 -10 0 l0 20 30 q0 ~ s

0

- !

I I - , i ] " ; ' I l ; t t l ' ' ' ' ; ; , t ~ ' ~ +!i -3 1 t l I ~ i t I; ,

ti ~lii ~ i l ; ' " : i

- q

LI 3 2

i ' " • " "

[ H i ' + . . . . . , ~ , : ~ . . . . t ' " . . . . . . I . . . . • : : ; ; l ! : t : . ' . . ~ : ~ ; . : : : . ; ! ~ : I : : ~ : , : i : : , • • ~ , - • • , , -% , ; . . , 4 .

i ~ - t i . . . . . | = ' ' ' t • : : ' " " : ' 1 1 " I , ; . . . . . . "~ - I t : i 4 i ; - : . : i . . ~ . : ' ' t ' : ' : . . . . . : . . . . .

t!1-I " ' ! ! " ' : ' : " ~ . . . . . ,+, . . . . . . I . . . . .

: ~ i l - i ! ! : : ; I . . . . . . ' . . . . : ' iZ!!~ t , : ; : : : : " ' I t i . - - . , . .

+t+ " ' + . . . . . ' I i Ti . . . . . . . . . . ' - ' "" . . . . . . . . . - 1 1 ; " t t V ' l '~ I " ' " t " " ' t • . I = , I - j +1 t 1 - t I t * | ' ~ ~ t ~ , ' . . . . . . 4 - .

, , i " I t " ; ' ~ ~ ; - " l l - , : l ; . . . . . '.-. " + ' , , , I ! , • ! .

+i ='+ ++:: i-! +.+ ::++ +::: l w ' ; - , ; + + + . , : I - : ! r l , " , . . . . . . .

i I ' ; : r , . . - : • i | ! ' " ;'T-T" 7 + . . . ? . : . , . .

, " , " ' ' . 1 ; t ' T T

,i i i , i+ i , !~t I:i! ::Ii 11 • : r F :

- ! -2 -3 -q C=

c. M= = 0 . 9 0 Figure 20. Concluded.

6 ]

AE DC-TR-78-4

$¥H H, ~n ~a ~5 % FUZE TRBS FIN GRP RedxlO -5 XNp SCALE El 0,5 0 0 0 0 NONE NONE NONE 10.80 39,33 0.25 A 0,5 0 0 0 0 NONE NONE NONE i , a7 3 8 4 0 0,2.5 e 0.5 0 0 0 0 NONE NONE NONE 1.81 38.20 0 .05

0 C.

- I

-2

-3

-q

C.

lli tilt ' 4. , , . . T:

.o i 1 _

it I i

II Kt • ., I • I i

I:*- il l il iii ill ~ .;.' • - - , , , ,

'.~I ! , i- • : • ; . r I

| ~ 6 i t . i 4 ~, ~-.

-qo -30 -20 - ]0 0 ]0 20 30 qo a ( $

~ " F ' t " / = . . . . ' , ' , . . ' . - i " ~ . . . ' ~ :-.,~ ~ - . ~ . . " .~ ' ~ I ' I , . . . : . . . . . . Z . . . . . . .~. - . ! ] ~ - ' : i : . ; i : ' : ~ : : l ~ : : : LI-'...~ ":..... . . . . . ....."-

i i l i i ' 41 ~ i I : . : . ] ,-; .~ i t - " , " T ' t . . . . ] " ' * i • .* . ! ~ - . ,

i " : ~ ' - ! i - : ! ' " # t " :-,.,d/t ,~ • ,~ . . . . ,-.

i~:: t Ir i r g : :-:4. 0 i t ! ! ; ~ i , i =" ; ; : ' . ~ - ; ; i

" " I ;4 ; i ; " i ' ! ! - t ' . , . _:..... i : ! r ! 1 t i ; i . !-, , ;

~'5i i i ' ! ~;~II :.t ' , : : : . i l . . . . . ~" I I " " ! ,.: . . I t - ; " . , , , . , , . , -~ l , . . . . . , ; - . -

l : i i l i ' , i i l . i i , i:t-I:i ' -~- - ' . . . , , . ,_, . - ' - : ' ; i ~ . ~', , i ~i.i Ii-li ! . - i ii.i~, , 7

. . i . i ; , . i . .

LI 3 2 i 0 - ! -2 -3 -q C.

- I

-2

-3

-LI

a. M= = 0.50 Figure 21. Effects of Reynolds number on the MVB

static stability.

62

A E D C-TR -78-4

STN 1~ (km lkz lk 5 ~ FUZE TABS FIN GAP Recl = I0 -5 XNp SCALE

rn 0 .7 0 0 0 0 NONE NONE NONE 8 .03 37.57 0.25 A 0 .7 0 0 0 0 NONE NONE NONE 1.82 37.10 0.25 0 0.7 0 0 0 0 NONE NONE NONE 1.38 37.00 0.05

lil)rllmt +it t : ; i " " ' "

o I: . i l i l ! :::

' I i + : "+,, : °

+ , + * t 1 t & i 1 4 • . o ° .

; . ~'.T 4 -3 ~ I - i t , *T !

i

-qo -30 -20 - tO 0 10 20 30 qO ¢ ¢ $

~ H . , + : . . . + . ~ , ! , = , . ' : - . . , t ; ~ . . . . + . . . . . . . - ~ ' ~ t - 4 i . - I - + • • + ~ • i • " ° * t + . i ' + + -

H .. . . + "1 + " F +I: " : . . . . I . . . . . . . . . . . . . . . . I . . . . . . . . , • r 4 ; ' ~ - , ; . . . . . ; + . . . . t . . . . . k , .

2 • • . . . . t - = • [ L - + . : . . . . . t

• . . . . *, r " i 1 1 : ' : ~ ( ~ / t ' I " I : 4 - ~ . [ . . . . . : * t ~ " ' ~ ! ' ~ ' " ; r : " , , " ' T " , : . . . . . . . .

I ! t - ' - f " ' - ; ' , T ~ , ; . - . ; , " ; ' 7 " " - !~- : "~; . . . . . . . i-i--.-i- ~-i i - i i ~.-i-;' +-;~ : _.u; : ! ;+ _:- : ;~ ; I ;-. ; . +t+:,- , - ' . . . . . . . . ...., ~ . . . t+,. . , . . . . : : : : • - : , - - .~ , ' I l - . : - ' - l - - - i - - ' ' I , - , - - : - . i - - ; - : ' - i . . . . ,_

0 P i t t - , , I . 1 , . , I , I , . i . . t , "

c. , . - , + : , . , , - : + ~ , , - , - , , + . . . . , . + . t i" i i- + , - r , i ' ++ I / " ' + t~ !_ . . IT : : l-: ~ = : ' t I. " - t .- ,- t- : t i 't ; i-i i ,-" " - 1 ~

- I

i l l ! E l i : +l.-.t ! ; ! : i ! " : ~ ---,-,, :',r'l'~ 1 i t + " . .

+!i ,+ . . . . ' . . . . * : . . . . ++ -+ i - !) + +i+ +, + i : ! ! ' . . . . . - i " l + * p i " t . . . . . . . . , - , . . . . , . . . . . . . ~*--I-+.'

+~. .... + " ! H+ , , , , p , i .-+ H .....

_ , . ! ' i ; : ~ i - - ~ ,, t:: i i : ] ! t LI 3 2 I 0 • -I - 2 - 3 -L

It_

C.

b. M® = 0.70 Figure 21. Cont inued.

6 3

A E D C - T R - 7 8 - 4

5YN 1% t I ta t l • FUZE TflB5 F I N ClIP R e d " l O "5 X N p SCALE'

0 . 9 0 0 0 0 NONE NONE NONE 6 . 6 2 3 9 . 6 8 0 . 2 5 & 0 . 9 0 0 0 0 NONE NONE NONE 1 . 4 8 3 8 . 9 6 0 . 2 5 0 0 . 9 0 0 0 0 NONE NONE NONE i . 5 8 3 8 . 6 6 0 . 0 5

, ) , , ,me ! _ l ~ ) i ' ) I | | • • i i . i .

l i i ..... ' . . . . i : i I ' " ~ i i - : : i ' : ! : : ~ i ! : t : : : ! i : = j i ' . l i t . . . . T , • ' , . . . . . .

l ' ' ' ! 1 1 ~ ' I . , f i . . . . ! f ' ' , ' l ! . . . . .

. i . , ,- , . . . . . . . . ! . . . . ' l f r ' . I . . . . 1 . . . . ; i l I : I I I " ' i ' I = :.,"~/ . . . . i . . . . t . . . .

" I ! I I ; ' , " I ' ! ' I , L B ' ' ' I . . . . I . . . . I . . . .

i.~r~,+ .., I . . . . t " " . . . . l ~ ' " : " ~ . . . . I . . . . . . . . . . . . , - , . . , , . i l . . . . . . . . . , . . . . . . : ! : , , - . , . . , . . . . . . . , . . . . , . . . . , . . . . , . . . . ! : i l i l l ; " Y . . . . . . . . . . . . . . . . . . . . . . . .

- i ! i - i t i - l i i : t . . . . . I . . . . . ; : : . . . . i " : ' : , 1 , 4 t "~ i l e • , I • • • , ' " t " ' t " • . , J P • • • •

• , , - t - + , ~ / : . t . . . . I . . . . i . . . , ! . . . - i . . . .

It-i-r ,i-,i ) ' : ' ' I . . . . I ' ' . . . . . . . I . . . . I ' ; ' "

• T : i T . ' : , t . . . . . . . . . . . .. . . . . . . . . . . . . . . . . T i,. ~ ' i : ; : ' . 1 : : : ' . 1 : : : : 1 2 : . . . . . . . . . . . . , I !- ' : I ; . . . . . . . .

3

i i-~ " " r ' + - i • t • ' • • | * . . • I ~ , . • m * • : ~ . - - r . , . •

t t ' i ' " + t ~ . . . . . . . . . . . . . t , " . . I , # : . . . , i . . . . . . - i l - q 0 - 3 0 - 2 0 - 1 0 0 10 2 0 30 q 0

C ¢ $

3 _ ; _ i . i . . i ! . . ~ . . . . ; , . ; ; ; . . . . '

. . . . . . . . . . . , i i- iliT! !1 !-i:ii !

" i f ; " - ' t " " ' I . . . . . . . . "~ . . . . . . . : . . . . "+t-t .... *,' "l"" "I ........... ' .... t ..... Irl'l "+i+l''!'l i,4'', ~''' l-i''i -~i .... I .... t - - . - , - - t 4 ( I . - i ~ , I i ' t I - : i . . . . . r - * - i - * . - T - . * i . . . . ~ - *

' ' - i ' ~ ' ' . i - I - ' . . ; : ' - . ) . i , ! , ' , , " , I - . t • + I : " " I ' " i " ~ ' - t • t t ' " d " " ; " I " t - . . . . . . ! • • I r - t ~ -

. . . . i i ~,,+'~ ; ; , , ' " : ~ - t ; , ) . . , " : / - . - H " . " ' ' , l r ; - - ~ ' " ' : . " . " . ! ' I ' ' : / ' : ' ; ; l ' i ! ' ~ . . . . . . . .

- 'i;- ' i ' i ~:" ~i , - . . ; ' ; - ; - ~ i ' ! ' " " i i I i i ~ l i i . . . . . . . • = " ' l- ! " ~.-f ~-~-" " " ' t l " i i ' t l " i t " t ' " t l " ; - I " : " ' ~ i ' ' "

. . . . • I "I ~ ' " " - 2 + " ' " ' i T r " ' ! , . = I' ?'-r " : . . . .

! -i-; ! ' ; i ~ ;-: ;-i-:-: . . . . i

. . . . i { i ' , l i iii' l . ! i I ~ " i l ~ ~ ' i

. . . . . . ~ i -1 -j 1"; T i l-; i ~ -, . . . . 7: i': r _~ !i i : ' i i : . ! ! ' t . . . . , , "

"' i,ii 'iii ' i l ,. : i~.,,, ._ , ,' ! - ! iH-~t LI 3 ~ l 0 -I -2 -3 -il

C.

0 CN

0 CN

-I

c. M = = 0 . 9 0

F i g u r e 2 1 . C o n t i n u e d .

6 4

AE DC-TR -78-4

5)'H po,, t n i a % % FUZE TRBS FIN GRP Reo=lO -s XNp SCALE

B I , I 0 0 0 0 NONE NONE NONE 6.31 35 .66 0 .25 ® i , ! 0 0 0 0 NONE NONE NONE 1.65 3 5 . 0 0 0 . 0 5

. . . ~ r t t ~ ~ I I , ~ I i . , ~ i . ~ ~ i I ~ i , i | , • • ~ I i ~ ~ ~

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. , , ; ! ~ I , . . = . 1 . ~ . ! 1 ! ! ! ~ : ) ' . : : I . . . . I . . . . l l . - i - ; , - . .

, , - i i i . . . . . . . . ' ,,= .J . . . . . . . . . . . . =!i!!=:.::l::::

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-I ; : ; ~ - . : ; i ~ . : : : 1 . : . . , . . . . ] . . . . 1 . . . .

. . . . . . . . , ..,~" ; i ! i l i ; ! i ] ! i ! ! i ! i ; ] i i ! i o ' * t o - ~ t ' I

- 2 ii!il;:iig.:::.!::l:i!:li!::i:i!ii::i! :::::::::::::::::::::::::::::::::::::::: - 3 I : . . . . . . .

T O , O l O , , O l . . . . I . . . . I . . . . I , , . - I . . . . = , , ~ o ~ t o - o o t . . . . t . . . . I ' , ' o p o o . , D , ° o , | ° - , . , , , , 1 , o , o l . . . . o , , , , I , , , , w , , , , l , , . , I , o , .

l U ° - , , I - ° 4 , I , o o I . . . . I . ° , O l ° . , o l , . , ° l . . ° .

-qo -30 -20 -10 0 IO 20 30 qo

. t I , . . , , ,

1 , t ~ , t . - ! T

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q 3 2 I 0 -1 -2 -3 -t C,


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A E D C - T R - 7 8 - 4

SYM

O [3

M . a 8, 3 2 B3

0 . 5 . 4 0 O O 0 . 5 4 0 O O

~4 FUZE TABS FIN GAP O NONE N O N E NONE O NONE YES NONE

H . L .

5 5

C,

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4 ,-I-~ 44. , i . ; - ~ , - ( , 4 4 - e,

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' r t ' ' + ' '

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Figure 22.

• i ~ ~ ' ~ t - ~ • 6 - . . ~

~ : ~ t ~ : ~ , i ~ : ; ~ i . . . , . . , , . . . . . . , , . . ~ , , , ~ i ~ . . t . , - . ~ .

I I I l I I ~ l J ~ t ~ l , . . l . ~ e l • t l l ~ ;;::.:.--::-: . . . .

. . . . ~ , ' ~ l l , , t , , ,

~ . ..~. iLf-i ' I ' ':'' ~t ' t I t ' ' l i " !I

1 1 ~ l . : l l t t t l t ? * ~ . - * , . , * ~ - * , t t t * l : ' ! ' l t * ~ . . . . . . ~ | ~ . . . . . . .

- ~ ' e t * . ~ * , • * * * • - t ee -~

t i ! l ~ !~ ! ! ! t

t i t ) t t t i , i t p ,

t - q P I . 4 ~ . 4 " t ~ - ~ - '

o . - - o # * * i i D ,

P,t """ • .' 14 ":i t*t I' t "o-t ; t 6~÷. 4- iJ , ° ' ' : t 4 - ~ ,

t * , t - ; - ~ * i ; : : • . f - t # ~ ; t ; ~ f

t t t l " ~ t , ' t :

" • f t ' t , , i I F I . . . +

7 8 q I0 II 12

Zp

a. M = 0 .50 Aerodynamic characteristics of the MVB in the FAC flow field, fins uncanted.

66

AE D C - T R - 7 8 - 4

SYM M . ¢1 ~1 ~ Z ~ 3 ~ 4 F U Z E T A B S

O 0 . 9 0 O O O 0 NONE NONE

, o 7,', ],,,,,,,,,,.,.~,,.,,.,,,..,...t i !t!t.~... :,,- " ° ' - . , i-*- f -~ *-- ',i-H--.i-.~ I l-v~. i.'-- t ~,~.~.

_ ., , t , ,~t t . . , . , t.t,~ .~.t ,..~!. ,.t+ [ ~ ! i ~ , . ~ +t +... t t 4 . t~t+. 1:, !, I . . ~ t : . . . t ,4 ,.,

n i ,+- ! - t i t i t ! - t t t-! l ) t-.hi t-i t# t ;+ ' t t : i t ! -' "~. ! I ! + ; " i t f l~ .1;_.., . ] : . . , . , , i . . . . . , , , 1 - . . ~ . i ' fm.t~++~t.tl,l,.,.:t~..,t,~,.t::.:l,~+t~t,~

- 2 . 0 ~tt1"t~"t'fil:'t'tttt°~+l*"~tl+ " I , ' I : , t ! + t +t+,

FIN GAP NONE NONE

H o L .

5 5

C~

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i l l 4 o : t t ' ' ' ' t ' : ' ~ . , . . . , , " i t : ' * . : , : ' . . " . ' . : " ~ t : t ! . - . , i

!it '~' " ' " " " ' " ' . . . . ~.,+.~ i . i ;:'.~1:

i . . i , ! : : _ , t ' . ' . ' t , i t ; i t t ' i ' ' t t : . " - : " .

0 I 2 3 ~I 5 B 7 8 9 I0 I I Zp

b. M =0.90 Figure 22. Continual.

12

6"7

A E D C - T R - 7 8 - 4

SYM ~ a 81 O I . i O O I'I l . l 0 0

82 83 84 FUZE TABS FIN GAP O O O NONE NONE NONE O O O NONE YES NONE

H.L.,

5 5

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- , , t °, ' a 4 . 1 l . . # 0 , e l i , o c t , i . , . i , p t o / / ; # . ~ 1 ,11- . e 4

- . . . . . . . t ! . ~ . ~ , ' ~ . ~ , : , . * t * : . ~ - ; ? ; . t . ~ T ' ~ . f " , - ' ,

. t } t t t t . . . , . ~ , l . t . . , , t , . : . . t : , ~ t l " t : ' t . ' ~ . . . . . ~,

H~t , ~ . , . t : . i , ~ . . , ~ t ~ , ~ . t : , ~ , . , , " ~, ' I , ! r t :*:: . ~ :

z " ~ r ' l ~ "~ ' t " . . . . . ; e , t ' . I ; • • t , I . ' " t t , . . . i f t ~' . . . . t ÷ "

~ . , i ~ - . , I . . - . l . . . . l , ; . . I . ÷ , , . l . , , . . . . . . . . . ~ . ~ - , . , . . . ;

] 1 . ~ l . . . . I ~ , . . 1 . . . . I , . . 1 ~ ' ¢ , ' ' ~ i " ' ; + " ' ' ' ' t ; ~ ' 1 . . . . . . i , . t , . | . . • _ ! • ! ~ ~ i . i . . . . • . . . .

i t ; ' ~ , . . * t ~ " . . . . . : , . ~ 4 . . L . . . . ~ . , . . . ~ , . . . ~ , ~ . , . . . . .

l 2 3 LI 5 6 7 8 9 ]0 l ] 12 Zw

-| ,~-.

c. M =1.10 Figure 22. Concluded.

68

A E D C - T R - 7 8 - 4

SYM

0 I-i

M=~ a 81 ~2 ~ 3 ~4 FUZE TABS 0 . 5 4 -12 -12 -12 -12 NONE NONE 0 . 5 4 -12 -12 -12 -12 NONE YES

F IN GAP H.L. NONE 5 NONE 5

C.

2.0

1.0

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Tt--t-T ! ! M -

~. t-i i ; .I . t .

' I T ' T

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r l ~ r , . : " 2 ~

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• _ ~ 7 : l ; 2 2 2 I ." ] : ? n S n . " • . . . . . . u

1 . . . . . . . . . . . - - - _ ;,. t ? J - ' ' I T i t ~ ' t ~ " ' • lb , . I I ' " T ' ' ' ' ' : ~ '

. . . . . . , , , ~.. ' l '~," _,i_

; ! i . . . . . . . . . . . . . . . - . ; , . , ~ i . . ; " , . , ~ | . . . . . . , . | . , . . . . ~ 4 - . . r ' - "

i , : ~ - ; . . i , i , ~ , . . . . . , . . . . . , ~ ' , , T * . . . . . ' ; - , , . . . .

• [~-[~ Tit , " - , ' " . . . . . : . , . . . . . . ' . . . . , " ' " " ~ ' , , , . , . . . . . . . , , ~ - " ,

| , ,t, ,I ,/, ? ! , , [ ,

~ . , ; ; . ~ . . ~ . . , ' . .; . . . t ;*~ ]~ " . . , , . . . . . . . . . . . . . . . ! . . . . • t .-~T; ; : , . . , .~'~",..

1 . . | i . t ' t ' ' " , " ' : ; o f t * " ' ' r , t . l l ' ' , t , t ' ' " " . , ~ . , ; - , ; ; ' [ . f T t : ; 1 1 ~ . , o f ? - * , . l . . . - ! . , . ~ ,

0 1 2 3 q 5 B 7 8 9 10 11 Ze

a. M = 0 .50 Figure 23. Aerodynamic characteristics of the MVB in the

F4C flow field, fins canted.

12

69

A E D C - T R - 7 8 ~

SYM Mm a ~1 B2 ~3 ~4 FUZE TABS FIN GAP H.L. 0 0 . 7 2 -12 -12 -12 -12 NONE NONE NONE 5 [3 0 . 7 2 -12 0 0 -12 NONE YES NONE S Z~ 0 , 7 2 -12 0 0 -12 YES NONE NONE 8

CN l i, • _ ~ . ~ " t ~ - t - t l . O t~ - f . t : ~ : - 3 + t 4 : . ! t , : . : ' ~ ' , . . . . . . ~ , : = ' i-

,( ~i.4 I-~+~ . . . . l i f t ' ; " . ~ , . ~ t ; , t ' ; " ! . . . . ~ ; ~ " t ' : t t t : ~ f " ~ ' : : " : ~ ' , ' 1 " i , " ' ~ : . , . . . . . . . . ~ - - , : ' - - - ~ . . . . ~ . t , , t = , t , 1 ' , . ,

: ,;~.. :::::::::::::::::::::::::::::::::: ..,.:l;~ ....:::: ,,.;~;;; - ~ . 0 ! ; ~ r t - , . - t . . . . ~ - I . , , . ! . . . . ! . . . . t . . . . t . . . . . . . ' . . . . . . t ' ~ *

Cm

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- e = ~ 4 I * * * ~ i * * 6 , q o : . , , i = o f ~ o , w , ~ o e o ? o . . o ~ , ~

] . O l - I f t ~ ' ~ , ~ : : = : , I . . . . . .

0 * ' ' ~ " - , . . . . . ' . . . . . ! . . . . ' . . . . ' . . . . t . . . . . . ~ ' 1 . . . . | " + " ~ ! ~ i ' . : ; ; I . . . . t ; . : ; ' . . . . . ';,.:t::-.t.;..t:;;.t..:;'....t:;;; ~I Q , l o l t * . o 4 * ° , l * , . * t t o - | o l ° 1 6 1 o * . | . t + l ~ , , . i ~ i * . ~

~ , ! i : _ I . . . . . . . . . . . . . . . . . = - • -

- 1 0 i , . , , [ , . , . J t , , , . [ . . . . • . . . . . . . 1 . I i i ' . . . . . . . ' . . . . . . . .

: , ; . . . . ; . . . . . . . . . . . . . . . . . . . . . . ::::::::::::::::::::::::::::: : ! ' ! ~ I ~ ' ! "'!~l:'~:l'~::l:~!'l:~'!l::::l:!:~l'~:'t':':l': ~ " -2.0 : . . . . . . . , . . . . . . . . . . . . . . . . . . . . . . . . . . . . r . t t . ~ t t , . , , ~ . . . I . . . . I . . . . i . . . . , . . . [ . , , . i . . . . , ~ . . 1 . . . .

' ; ;; . . . . . . . . 1 . . . . i . . . . I . . . . ! . . . . . . . . . . . . . . : : : I : : : : - 3 0 . . . . . . . . . . . . . . . . . .

0 1 2 3 ~ 5 8 7 8 9 1 0 1 I 1 2

Z p

b . M.~, = 0 . 7 0

F i g u r e 2 3 . C o n t i n u e d .

"70

A E D C-T=R - 7 8 - 4

CN

SY M Moo

O 0 . 9 D 0 . 9

A 0 . 9

0 0 . 9 2 . 0 . . . .

i i i i 1 0 : : : : • - = ~ , - . e - ~ 4 , .

. o o o .

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0 0

0 0

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i •

t *

8~ ~ z 8 3

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- e - e e , - ~ ] - e e e = ~

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~ . i ~ . , . , i i - ; ?

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" ' : ; : i i ; ; -

~ l * 1 ' 1 7 t * ' i~: ~'~ . . . .

~ 4 F U Z E T A B S

-12 N O N E NONE - 1 2 N O N E YES

- 12 YES Y E S

- 1 2 Y E S NONE

: : : : : . . . . . . . ~ . . : h . - : l I . ~ I . ~ " ' ~ r , - . t ' : r t ~ - . . ' f l r t t f H

-e e - ~ . - e ~ . . . . . . . : : ~ : . .~ .~ ,~ . . . . . . . . . . . . ! t ~ i t t : .~ . -

• ° ° ° ° . . . . . . l ~ ' ~ t | * - t ? - ? '

. . . . . . . . . . ~1~! .~; . t . . , ; ; ; , ' i i ; ,

L . . . : . ' ~ .

FI N GAP H.L.

NONE 5 NONE 5

Y E S 8

Y E S Ii

. 44 -4 . 4 -1 -1 -4 -1 -$J , - 4 .~ . • - e - - e - e 4 d l - - I , - - I P -41 - e - - # - i - - ~ -

~ ' ? " "t '? T l - f ' ~1" *_ .?"

. . . . . t i ~ . I { 1 ~ ! : - • ~ . e - - e -

- e - , e - . ~

~ . , ~ ~4 , ' ~ tt. t ~ . . * , ? * * , . - , - o .

" ' * _ . . " t * ; T ~ ' t T-

n = n , |

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. . . . - ~ 4 ~ 4 : - t . ~ . , . . l ~ { ' ÷ - i ~ i - - * ; I - . ~ ; : ~ ; t ; - ~ - ; ; U ; . ; ; ~ ' . ~ ' ~ ; - ~ , - ' ~ . . . . . - ' ~ , ~ t _ t . _ ~ . : ~ . . . , ~ . . . ~ . . , , _ _ . _ . , , . .... 17"" t ' t t • t "1 ~ , ~ ~ . ~' . . . . I t " l I " ' | . . . . t ' . . . . . , , • , p~ ~ . . . . ~ -i

- ' - '4- , - - - i i I l : : : = ' : : ~ , ; - - ;;: i . . . . , ' : ; ~ ; , i : : ' : ; ; ~

, i . . . . . • e , i e . '

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• . , I . . . . . t . . . . t , ' ,~ . . . . . . - , . i o • ' ~ ' ~ • ' t . . . . . . . . . t ~ . , t : . . . . t . , ; , t . • ~ . . , • . . ~ . ; ~ _ ~ ~ . . ~ . : n , ~ _ ~ n ~ . . . . | . : , | . . , . , . ,

I • - - r ; I " - | " ; " ; " - • ; . . . . . . . . . . . ; - - ; . ; _ _ _ , i . il~, . • t . , • t , - i . . . . i . . . . 1 . . . . | , . . t l . . . . I . . . . l . . . . 1 . . . . i . , . .

- - . . - . , , " ' - ' ' ' " ' . , , , . , ~ . . . . . . . . . . . . , . . , . . . . . " • ' . . • • " ' ~ ' , . . . . . . . . , " ' " " ° ' " " ' " " " t . . . . . . . ' , , , . . , • , , ~ . . , . • . ' ~ . . . . . . . . . . . , . ~ . . . , , , ' . . . . . . . . . . . . . . . - . , . . . . t . . . . . . . - . • t ' ~ ' . . ' - .

. . . . {~ . . - ~ , . . . . , , ~ . I . . . . l , ; ' ; l ' - ; ~ t ~ " . i ' ~ , , i . . . . . . . . , . . . . . . ~ ' t ~ " ' ~ ~ ~ " l ' * " | t I " • f ~ ~ ~ I f ' " ~ I i • t " " 1 " ~ ~ ' r t ' ' ' t , , ~ * t ~ - , - ,

, . . t 4 . . 4 . . ~ . t . . ~ . | . , . . | . , . ~ | . . . . | . = . . i . . . , | . . . . , . . . , . . -'m-, ~..~t " ' T ~ , ! ' l , , t • t , , • , t . . . . ~ . . . . . . . . ~..,~ . . . . . ~ , . . . . .

0 l 2 3 Lt 5 6 7 8 9 l 0 11

Ze

c. M= = 0 .90 Figure 23. Continued.

12

71

A E D C - T R - 7 8 - 4

SYM M = a (~i ~ 2 83) ~ 4 F U Z E T A B S 0 I. I 0 -12 -12 -12 -12 NONE NONE E] I . I 0 -12 0 0 -12 NONE YES

FIN G A P NONE N O N E

~ L .

5

CN

m O | l l ] m E

-! .Q~ _2.0u.as.~

I I ] I

~ m

,

- • 4 -

; : : : l I i : : l . . , .

~-1-+* I + ~ 4-. + * i-,-,- r-+ f r I t l +- i-th+ i "" i-i ! ? i *' l'++f. $

• ~ t" J'?-@ i, 1+-¢-1.*

~;)llj+, ~ + ¢.~-+ ~+'1'½+' t t +'+,

- , , t t . - . ~ . t t t ~ - . • . T * . I - ~ o ' t * t * * -

I. 0 m-~J~-kl

oI!~ c. I ,~

TF/) ':

,!i -~'°t!i:l -3.0 : :

0

t s

~ ._-,,

i ! .

++hl;H; T ' t t l ~ ' t

l . = & I , - .

,.,lJl, o ( ~ o + t

~ t ~ t t * • ~ ' ~ ' ' _

e t l t l ) ~ t " "~ " : l

' ' ° ! I "

I 2 3 4 5 6

: " ~ I " : ' I ~'~'I::'~I: I !1 -' , , ,

~t t '~t -~*~ ~i~i ~ , . , : ; ; : - ' ' • ' ! t I

• , , . . ~, i . ; ' : : : :~ - : : t ' ' ' [ " , 1 l . t - . ~ ° t . r . - - I

+ t t • ~ t t t • • ' ~ ' t . I . . . !

t l t t I • • *..e. ° 4 D ~ o - t 9 s t ~ t t t ¢ ~ ? 9 ~ t t

7 8 9 I0 II 12

Zp


72

AE DC-TR-78-4

C A

2 .0

0 1 . 0 ' A

B

ol

SYM MaD r, FUZE TABS FIN GAP H L

0 0 .50 4 NONE YES [] 0 . 70 2 NONE YES

0 . 9 0 0 NONE YES 0 1.10 0 NONE YES

I , I

NONE 5 NONE 5 NONE 5 NONE 5

I 0

C N

0

- 1 . 0

I

I l I i I

2 .0

Cm

1.0

0

- I .0

Cr-- i i

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

L " - " - "

- 2 . 0 , F : = = = ~ ~ ~

- I 0 - 12 0 -2 - 4 - 6 - 8

Figure 24. Variation of the aerodynamic coefficients of the M V B with fin cant angle, two fins canted.

"73

A E D C-T R -78 -4

SYM M= a FUZE TABS FIN GAP H.L. 0 0.50 4 NONE NONE NONE 5 o 0.70 2 NONE NONE NONE 5 Zl 0 .90 0 NONE NONE NONE 5 0 1.10 0 NONE NONE NONE 5

2.0 1 ! I cA I '

"°'! ' i ' 0 i

0 t 1 i

- 1 . 0 1 I

4

2.0

Cnr

1.0

0 f

-2 .0 I ~ ' ~ 0

f

I

I

J ~ i I

I

I I

I --r_t r

I

--2 -4 -6 -8 -I0 -12

Figure 25. Variation of the aerodynamic coefficients of the MVB with fin cant angle, four fins canted.

74

A E D C -T R -7 8 -4

SY'U

Q

&

¢,

x,81ii:i

14,, = TFIBS I z I,, a I~) ~ TER CONF AIR. 0.5 q NONE 0 0 0 0 I I F-q 0.5 q NONE -3 -3 -3 -3 I 2 F-q 0.5 q NONE -6 -6 -6 -6 l 3 F-q 0.5 q NONE -9 -9 -9 -9 1 q F-q 0.5 q NONE-12-12 -12 - |2 [ 5 F-tl

, ' [ - I i ] . | . | i l l

. . . . . . . ° ° i I t l

6 '1 I ' - i ~ * •

f l i T ' ? !

t t f t ~ ::: , o |

i b o t ! J t

t]Hir t . . . .

60

50

qo

30

20

Ao 10

OI

-10

Tp q , 1 : l l , i ; I ~ ] -

L~i-.

.q I - ~ - t t t I ' ; ! ; " --

-20

-30

-q0

-50

-60

'20

16

]2 Zp

8

q

0

IIII ' ~ I ~'~ ',:,:,i i i ~I,LI . . . . 1 l l i ~ ' I ',

; -;_;-;- - -1- L-,-;-

- ~ , ~. :_-~ -i. .~.-.- I

. . . . - r . t - -"- ~ . T .

0 0.2 O.q 0,6 0,8 l .O

30

20

At [0

0~

- I 0

-20

-30 0 0,2 0.~ 0.6 0.8 l ,O

t

a. M = 0.50 Figure 26. Wind tunnel separation trajectories of ;the MVB

from the No. 1 TE R station of the F-4C aircraft, four fins canted.

75

A E D C -T R -78-4

SY'M

(9 r:l &

O:

-q Xe

-8

-12

-16

60

5O

qo

30

2O

10

Oa

-10

-20

-30

-qo

-50

-60 0

M, = TABS I n 0.5 q NONE 0 0.5 q NONE -3 0.5 q NONE -6 0.5 q NONE -9 0.5 q NONE - [2

. J - * *

: n i - , - 4 .

i i - I

- t - ~ •

I a #,,m N TER CONF AIR. 0 0 0 1 1 F-q

-3 -3 -3 1 2 F-q -6 -6 -6 1 3 F-q -9 -9 -9 1 q F-q

-12 -12 -12 1 5 F-q

i

I ! " ° ,

t t ' " ! ' l

i 4 i o - i q

- i ] I . . . . . l

: '. : :

. . . . . . . :i . . . . . . . ! 1 " -

1-1-1 ~ 1 1 * ' o " * " t P t • , -!.,,-, r : ;

- , - - ' 4 - t - ~ - ~ •

I

- - P - I ~ e , - 4 - 4 - - 4

- - o - - o ~ , - , t - ~ - 4

- - P " 4 - - ~ - , - 4 - - ' P - 4

~,,-

-.,,_;_; ,_ .

II~-4 - t ' - ~ " ~-~--1-1

.L~.,L ] -J '-- i

- 4 - , + - - t

- I - 4 - - - 4 - ~

: : : : : :

: : : : - _

- o - - , - ~ • o - ,

- - 4 - + - 4 ~ ~ ,

4 " t - - ' l" 4 - - " 4

L-i.-i..i. :L.L,

q 8 12 Zp

16

COLLISION BOUNDARY

3O

20

I0 At

0

-10

-20

-30 -8 -LI 0 q 8

Tp

a. Concluded Figure 26. Continued.

76

A E DC-TR -78-4

SYM ~ = TRB5 en ~a l) ~ TER C0NF RIR. e 0 .7 2 NONE 0 0 0 0 I 1 F-q B 0.7 2 NONE -3 -3 -3 -3 i 2 F-q & 0.7 2 NONE -6 -6 -6 -6 I 3 F-q

0.7 2 NONE -9 -9 -9 -9 I q F-q 0.7 2 NONE -12 -12 -12 -12 I 5 F-q

-Lt Xp

- 8

're

i . i t t . i i

OI " ' : " ' : : : :

4 " " "

1- I I I : : : , : , LI] , : ~i- ~ i i

- I ~ ~ ! i " , - , , . . J l . . . . I . ! l . . ~ l . i

~"i ! ' ~ i I ~-: i i , ~ ,. ; -

~J I I I I l I I I I I l I I . ~ . l , , I I , I l l , ] ] ] " ' "

, . - -

_q ';-;

60 l l i t [J t : i : H - L i i i : t l t t : ' t ' + t - i ~ - . [

" ' t ~ ' " ' " ~

5o I I I~ ! i , i l l )~i t 1 I I : ' t 'T-,v • tt .~, ~-+ . ~ . l i . I i _ ~ i ~ t ~ qo i ] ; ' i ' . . i ' . : i =

3o !ii "=-i " '~ :~ ~!-;" '-'~ ' - " , : i.-! t " :

~! i~ ~ :"'

=.,o ~': ! - i ''-~ 7.i ~-~i .;::: i-.t~

-1o ~---i!~ N!~ , - - - " - " - ' • !-tt I~:~ i , , . ; ~ ;

~O ] . . ,

-3o +~" i '-.-; :~ : . , , ,~" .:_i-~.-:-.~-.--i-~ ;--.l~--J- • ' "T . . . . ] - t - , " 1 T - r - , =- " T I "T'r-" " I ' - I - . " : " * ~

-40 -~ i- --~ ~4-; i:~. ~.-~.! ~_]:V :~T~:'~-F"-,-.~,

-~o i; f b ~ ,

30

20,, I ,,,

I % - - " - + 12 H-I- . . . . . . . 4-1a Ze -~" -m- ~--

~ TT ~.-'.:- 8 ~ '+-.-'7 ~-

40~_ ~ .-! '..,,(,-F H-;- : " i t i : i

~i: -~= ' .~ 0 0.2 o.q 0.6 0.8 1.0

2O

lO AS

01

-I0

-20

-30 0 0.2 0.~ 0.6 0.8 ].0


77

AEDC-TR-78 -4

S ~ ® 0.7 i':1 0 , 7 A 0 , 7 v 0 . 7 O 0 . 7

Xp "q j _ 1!I:t

60

50

~0

3O

20

10

01

-10

-20

-30

-qO

t -50

-60 0

i TABS 2 NONE 2 NONE 2 NONE 2 NONE 2 NONE

~,j ~ % ~ TERCONF RIR. 0 0 0 0 I ! F-q

-3 -3 -3 -3 1 2 F-q - 6 -6 -6 -6 1 3 F-q - 9 -9 -9 -9 1 q F-q

-12 -12 -12 -12 1 5 F-q

Ii1, , i' I I m i t l - ! ! ! : ~ I',

I I 1~ ,1 I1

tt! , ! i - i f ' ;.;

- - r l - ! !-t ~ :

~! . . . . . , , i i i i

° II-Z ~ ' , . - i . ~-1 ' ~-i : t t t-I

-t-r " .L 1 - I - ' t P : : I _ I ! j -,j . , . J - . - ~ 1 . . ~ . J -

I . I - t -~ . . . . . . - 4 -

IM . . . . .

] I-I- - , 1 "I . . . .

! . ~ b - t - 4--~-, - ¢ ~ l -

i~J_~ _LI_ _ LMJ. :H:

i -L i-iJ..L -;J-

g 8 12 Ze

30

20

10 A t

0

-10

-20

-30 16 -8 -U, 0 LI

Yp

b. Concluded Figure 26. Continued.

8

?8

A E DC-TR -78-4

SYM

e B A

H! _,6I++41

Tp

11= = TAB5 0 .9 0 NONE 0.9 0 NONE 0 .9 0 NONE 0 .9 0 NONE 0 .9 0 NONE

10 ~a ~ t~ TER CONF RIR. 0 0 0 0 I I F-~

-3 -3 -3 -3 . I 2 F-If -6 -6 -6 -6 I 3 F-q -9 -9 -9 -9 I q F-q

-12 -12 -12 -12 I 5 F-q

';+"+' ! :i II! ~ ' ~ ! ! ! "! . .

i ; I +!i .. : " ~ i ! ! . : : t r - l t t P ' t : ! i : ;

t r r l ! t Pti+. ~Iº,,, . . . . . . ; " i ; ~ -

: - : : :1" : :I'11 :-:-;i t t l l ! t , I I + . . . .

. . . . . . +i ~ f ! | P ' " t L - o''+'.-..,

I | ' I I I I I | 1 1 1 1 [ I I I I ~ I I

i : i l i , ] + [ l l i , z l t 1 ~ l l l | i l l l i l i l l l l , l ] I t t f |

U t l ~

I_I_.L~LLL~tI~It~fI~LL.LI _~ I I I I I I I I I I I I I I i I I I l l l

60 .i: t -

5O i !

qO t i

L :t0 t

r

"Ti Jr"

~e 10

OI

- I 0

-20

-30

-qo

-50

-60

I I |-I-I-L I F 1 - I - 4 - 4 - I I I " # - l - I

, i , + , t i i | 4 | t

! ! ! ! .'.-,.. + t ~ - , ~ o - + .

-i # i - , - i - -t-+ i -~- +-#-

-H # -i -i-~ . - l - - t - # . t - ,i--,i+ -

- i - - t # . ÷ + - - ~ .

. o . . . .

=,.LLi-L

- + - 4 - - i - - - 4 - - 4 - +-- : : : : :

- i - -

- t - ' < ~ l ' - 4 - -4 - -+ - - - - I - - 4 - 4 - - 4 - - 4 - - I - -

; , : : : -

: ; : : : :

20 I

16 1

0 - 0

Ze 12 i i i i i i i i i i i i i i i

. . . . . . . I i_l.~i 1.1_1: i - i - I . ( , i , . i - e ,

1 l"l-tZl'TT t'l-l-t- r-r1-t I-I L3~I-I- I ;4-; -;- ;-;-;-;- L, Yi I I F! . . . . . . . . . . . . . . M-r t ' t ' t " t t -M-r r t - r r

0 .2 O. tt 0.6 0 .8 l .O

30 I I I I 20 , I I

10 + &$ -.-

o,~ T-

-tO ~- -4--

-20

-30 1- 0

! ! ! ~ ! !

i i i : ! i i i i : : i

! ! i ii ; : : : : : : : : : : :

- - P - I - + - - + - - k - - ~

' - I " ; - t - t - t - l -

- ~ . i -

- t . - ( - | - - | - Ir. I - - # - - I I - + - 4 - 1 . -

-M-PrM--

0 .2 0.~ 0.6 0.8 ! . 0

c. M . = 0 .90 Figure 26. Continued.

?9

A E DC-TR-78-4

SYM

&

0:

Xp -tl

-8

-12

-16

6O

5O

qO

30

2O

10

0,

-10

-20

-30

-qO

-50

-60

if. = TABS 6 i t a I, s ~ TER CONF AIR,

o., o ,o, , o o .~ .° I ~ ~-~'~ o. , o ~o~ - ~ - 3 "~ "~

1 3 F-q

ii[illlllllilil ilillllIHllHi ItiglllllHli iilHllggli

F-.

I i

0

o-.o

H • o

. q - ,

-H -M . | .

n n

I 8 12

Zp 16

30

2O

I0 At

0

-I0

-20

-30 -8 -q

l~ ] l W l l l l l l l l l l l l |

I l n l ] l l l l I I I V ' i ' i i in

L d i l [ l l l

0 q 8 Yp

c. Conc luded Figure 26. Con t inued .

80

A EDC-TR-78-4

SYM

0

D A

Oa

<)

-q Xe

-8

-12

-16

R. a TRB5 I n l a I s ~ TEA CONF R|R. I . I 0 NONE 0 O 0 O ! ! F-q !.1 0 NONE -3 -3 -3 - ] I E F-q I. ! 0 NONE -6 -6 -6 -6 I 3 F-q |, I 0 NONE -9 -9 -9 -9 [ q F-q 1.1 0 NONE -12 -12 -12 -12 i 5 F-q

t t l i ~ , - i t t t t ! ,'

il '

I J-l I ~tl i !

~. I i ! 1. tt ,~o

Ao !o

01

-10

Ye I | | | |U||==| i m m m u m m n m m m | t u n l i i n n i i i n l l u m B i s l l m n m I I I • • . . . | | .=| , |=l im inmunmnnmn

-20

-30

-qO

-50

-60

30

20

16

12 Ze

8

q

0

!

..--I- ,--.4.

,-i. i!

0 0 .2 O.tl 0 .6 0 .8 1.0

2O

10 AS

Oi

-I0

-20

-30

l i l N I m n m l i i l n i l i n l n l lmmnunmmmumnmnnmnnmn |mmmummmnmmmmmmmmmmn mmnnnmmnmmmmmmnmumn~

immmmmmmmmmmmmmnimim: nmmmmnnmnmnnnmmnnimn ummumnmmmmnimmnmmmmm | n n m u u u m n m m u n n n J n u u n ummummmmmmmmmmmmmnmml nmmimmumnmmunmmumnmul nmnmmmnmmmmmgnunnmmml ~..gmmm.~nnmnu mmnnmnmil . ~ m m n ~nmmmm mmmmnmmil n • ~ B ~ M l l m mmiBmmlm I iBLmim im l molto B I H m H R H I nmmnmmmunnmuniniuimnnnl nmmnmmmmmmmmmmmmmmmml mmmmmmmmmmmmmammmmml n n m m i m n l u n n m n u l m m u m u l umunummmummmmminnmmn]

mmmmmmmmmnu |mmmmmmmmmmmmnmmnmnml nmimimmmmnmmmnmm|mmml nmmmmmmimmiunmmnmnnml unmnunnnnnnummunmunu ]

0 0 . 2 0 . q 0.6 0.8 1.0

d. M= = 1.10 Figure 26. Continued.

81

AEDC-TR-78-4

ll'trl ® El ,,A V 0

o,'~

-LI

--8 ! I

-12

- 16

60

50"

qO

30

2 0 '

10 I 1

oi |

-10

-20

-30

-qO

-50

I

-60 0

M. = TRBS 1.1 0 NONE 1.1 0 NONE l . ! 0 NONE !.1 0 NONE 1.1 0 NONE

6j l, z % % TER CONF RIR. 0 0 0 0 1 1 F-tl

-3 -3 -3 -3 1 2 F-u, -6 -6 -6 -6 1 3 F-u, -9 -9 -9 -9 1 It F-It

-12 -12 -12 -12 I 5 F-ll

%11!i - i ; L 1 . ~ ! ! ,

ilq, :- t -

- - - ] / :T" ~-ll i

t ,~ | . i ,

4 " I " '~ ' ; I - "" '~ " - ~ ' T " TT

I ! i ! :~-- • t I - - t

1 t - t - i

.--i-; " ~ I 1.I~ 4~I ' 4-: i ] I , . I - ;

-r t"- ~ .

I-! -

t ' t - o i ~ - " l

: :-:: T r - i

', t-:LI: • - I - I ~ - " ,

-!- -F~ )~,-r-

--I~: ÷f t:_ti

~t 8 12 1 Zp

3 0 1 1 i ! I i " ' I I ! ' l l l L . I I I I l i

~ / ~ / I I I 1 1 i

I_~M_.I_] i i l t " t I I I I I ~ I ~''" i . ' _ l ! I I i

A ' l ' |_1 i 1 i I I

o I-FH+FF " t ' t H ' - f _ f f ' 1o I-:~-FFt--

I - I ---FkL!-,- I _o,,I-~--~,--

°" I f i T H - -ao I -H+FH-

6 - 8 -Lt q Tp

d. Concluded Figure 26. Concluded.

82

AE DC-TR-78-4

SYM 94,, ,, T1:185 I,z I, a ll~ I~ TEA CONF AIR. e 0.5 q /E5 0 0 0 0 I I0 f -q A 0.5 q TE5 -6 0 0 -6 I I I F-q v 0.5 q TE5 -9 0 0 -9 I 12 F-q @ 0.5 q TE5 -12 0 0 - 1 2 [ 14 F-q

I~ H ' t J l | - | 1 ; i , | ~i ' - l i I ' . - . , ' 1. 1 ~ r | [ ~ ! • • ~ ' t

o ! i r ~ . . ~,,+ :i, .q I!~ i ! r , ~ , ~ . :

x, -t I~' - t

i i ; ~ ... 4 ..... -12 ..... i " ~ i~ .~i i ~.'

-16 ] ! , , i~ +(. ')

'l'p

¢i ' , i ',~. ',,~ ;, ~ _ ~ . ~ _, ~-.~-~-~~~,-I

60

50

q0

30

20

1 0

0~

-10

-20

-30

-q0

-50

-60

Wlililtifl liillliiililiiH lllBlglllllU a i I l i l t

J/ B6 llilg iiR HHilblili InmiP !Igiii)Bl!li Immmlmmmmmmmmm mmmmmmm( imammmmmmmmmmmmmm( imammmmmmmmmmmmmmml inummmmmmmmmmmmmmmi

20

16

12 Zp

8

[i

0 0 0.2 0.q 0.6 0.8 1.0

3o I ~i:,

At lOoi ~ -IOL

I I I I

munnnuN immmmmmum ~ummuumn Iamnamun immmmmmm immmmmmm immmmmmm mmmmmmm :IL¶BJI mum .,~.~,.~ ~ m

imi=-~iimm ,mmnmmmm ,mmmmmmm immNmmmm kmmNmmmmm immmmmmmmmm immmmmmmm imlmmmmmml inmmmumm tmmmmmmmm ~mmmmmmm

0 0.2 0.~ 0.6 0.8 ] .0

L L

a. M = 0.50 Figure 27. Wind tunnel separation trajectories of the MVB

from the No. 1 TER station of the F-4C aircraft, two fins canted.

83

A E D C - T R - 7 8 - 4

s'Y~ H,. -, TRBS e,z l a % % TEn CONF RIR. e 0.5 q YES 0 0 0 0 ! I0 F-q & 0.5 q YES -6 0 0 -6 ! !g F-LI

0.5 q YES -9 0 0 -9 I 12 F-LI 0 . 5 q YES - 1 2 0 0 - | 2 I 14 F - q

0 ~

-q Xp

-8

-12

-16

60

50

qo

3O

2O

10

O,

- lO

-20

-30

-qo

-50

-60 0

, • " t I !

..T[ : : t : : : . . . . . . . ll-I

. . . . . . . . . I 1 - " - g I . I

: : : : : : U . . . . . . . . . . . i-& 4

. . . . . . . . . . . . . t" T"

n

,--+ + i o ~ ~. - , ~ .- t--ml--

. . . . . . . . . . . mr1"1 ' . . . . I1,-I-1

- ; - 1 - 1 - t ' l ~ " I , '1"1" : : : . : , .

. . . . . t J:~.L +,,-o ~ ~ - ~

. . . . . . . . . . F I - " T . . . . . L4-4-J,-

,-,~- -. , . - . . I : l - ; F~

m - - - 4 - ~ - . m # - 4 - ~ - ) - + - I - I .

. . . . . . . 1-14--l-, H- . . . . m i a m l m a l j L

i - - . . i - - t - - o - I , - 1 . - . . 4 - , I - , i - - i - . i . - . l -

F ~ F ! - ! - r r l T 4 : F

t-~t- ,-H-, ,'

~-i-H- F - ~ 8 12 16

Zp

30

2O

A, lO

0

I m m n l m i n m n n i n m m n m m m n ~ i u ~ m m m m m n mnonmmmim m - ' ~ , i i n m a m i l l n i N n ~ u m l u m i u u m u N n n k , a n m n n ~ a mmmmmmmmnmmmmni |mmmmmmmmmmmmmnm mmmmmmmvmmmmmmm

mmmmmmmm,mmmmmmm mmmmmmmm,mmmmmmm mmmmmmmm w~-~']mmmmm nmmm mummy". ~)Jmmmmmmm mmmmmmmmm, "mamma nnmmmmmm ~mnmmmmu mmmmmmmmmp.mmmmmmm mkmmmnmmm,mmmumm mmmmmmmm~'mmmmmmmn mmmmmmmmlmmmmmmmm mmmmmmmm~,.ummmmmn mmmmmmmmm,immmmmm mmmmmmmmmmmmmmmm mmmmmmmmm~immmmm mmmmmmmmnmmmmmmm mmmmmmmNmr, lmmmmm

- lO

-20

-30 -8


-q 0 q 8 Yp

84 t

AE DC-TR-78.4

syM i% - TABS I n %' % N TEflCONF'IllA. O 0.7 2 YES 0 0 0 0 I I0 F-tl A 0.7 ;~ TES -6 0 0 -6 I I I F-tl v 0.7 2 YES -9 0 0 -9 I 12 F-c¢ ~, 0.7 2 YES -12 0 0-12 I 14 F-q

O:

Xp

-8

-12

-16

!-fl!tlltll i-it . . . .

:Ht;I)i iiiiiii " ; i--~ 1-I )-1-I ?~'r

Y, q I - H - H + H + h ~ ~

H .q l l ~

60

50'

qO

30

20

1 0

Oi

-10

-20

-30

-rio

-50

-60

Zp

20

16

12

8

tt

! ! ] ?l)!)))

) i i ; i i i i ~ i

] I : ; : : ; : . ; :

i i i i i i it'k-~ ' ' ' I | | A I ~

-..I--I.-4

0 I ~ . . . . . .

0 0 . 2 0 . t I 0.6 0.8 1.0

301

2O

10 A t

01

-10

-20

-30

mmmmml mmmmml mmmmmml mmmmmml mmmmmml mmmmml ~mmmml mmm~

um.mmm, m,m..mm

r--dlim rmmmmm immmmm nmmmmm immmmm immmmm l~mm~ immmmmmmm immmmm lunmnm ln~mm

molml,.m~,~ moN~mIml;m p

b. M = 0.70 Figure 27. Continued.

85

A EDC-TR-78-4

SYM !I. • TRB5 *l *a $3 ~ TER C0NF RiR. e 0 .7 2 TES 0 0 0 0 l IO F-4 A 0.7 2 ~E5 -6 0 0 -6 l I I F-4 v 0 .7 2 YES -9 0 0 -9 [ 12 F-4

0.7 2 YES - f2 0 0 - 1 2 ! 14 F-4

0 I

-4 Xp

-8

-12

-15

60

50

40

3O

20

l0 Ae

01

-10

-20

-30

-40

-50

-60 0

I! it:lE

,F

'7. r. 1: 4 - -

t 4-

t

| . o

~ - ° .

I I "

, 0 " - 4 -

, - 0 O

" - - e - - - ( - "

- -4 - 4

i ,--o - * -

i - t - . .*-

i - - - I , -

N ! - , P - - I - -

! * - 4 - - u - - - 4 ~ -

P 1

I , - . + . - ~ -

t - t - - I -

I - - + - - . ~

t - q . - -+ -

4- t

I , - 4 - . 4 -

I,- - I,- + -

t . . 4 - - 4 -

8

. - o

i l -

Zp

I - - !

" T ' I . '

"I "~ !

"t11 t - - o

, - ~ - - t - , - q a - - I - ~

- F-~

o - ~ .

i

2 16

30

20

10 AS

0

-10

-20

-30 -8 -4

b. Concluded Figure 27. Continued.

0 4 Tp

86

A E D C -T R -78-4

sYM ~ ,, lABS mm ~ % % TERCONF'AIR. 0.9 0 YES 0 0 0 0 I mO F-q 0.9 0 YES -6 0 0 -6 I l i F-q

v 0.9 0 'fES -9 0 0 -9 | 12 F°q 0.9 0 YES -12 0 0 - 1 2 1 14 F-q

II -k llI.,-illl liil

--I. ........ L .... ,i I (k-i m4 4 ,m i 1, ,i

0: "7..i!il~I~ , i : : , |i o~

:I: t o, 11-

Xp .~. . . . . . . . . . _ . , 1 . . . . . ~ : l i !1

-0 : iiil i:i ; ; , ; - ~ - • -m .i ~ . i- • - ( . . (, i i . .4 .

-12 ,~-i~ i ~ ?!"?,

. . . . . . . . t l i i • +" +'o 1 :

Ye 1 I 1 1 I I II I li

I I [ l l l I i | ! l l l [ [

~ I ' ~ P ' ~ I ~ l l V l i J m - i r l [ l . . I I i [ ! ! l ) l l l l ] [ i : : ] : l i [ l I ) l i l l l ! l l ) I ] ) ! ] [ ! ) 1 1 1 1 1 1 1 : ; ; :

60

S0

q0

30

20

Z0

0,

- !0

-20

-30

-q0

-50

-60

Iiili IIiII

)fill

llii| Ill) i ::i!ii R)

,Ilmmml :mIIII I!mnmi imimIi

20

16

30

Ze 12

lmmuiimmmml immmnmmmmml immmmmmmmml lmmmlmmmmml

III--'IImllIl IIIIIlIIIll ImIIlmIllIi

IHIIIIIII I iiimmumni4ml ~mmmmmmi nmmmmmmmHl mmmmmmm~,

i m m m m m m ~ d l lmIIII~wmm limmiiipimii lIm)IlmlIm iNN )mmmmm

I)iiIIIIIll

2O

:~: I0 i i i A ~

.... I0 -.m..

i i i -20 III - so

0 0.2 0.~ 0.6 0.8 ! .0

mmnmmmmmnmmn mmmmmmmmmmmn nmI lnI Iumumni I n m m i I m m m m m m i

I I I i R m l l m m B | mun.mmnmmunnmmnn mIIn,,mnnmmul N N I N N N I N N I BIIimNImminmml

u~amnmmmnu I N I ~ | I I I I I mmmmmmmmmmmm mmmmmmmmmmmm mmmmmmmmmmmm mmmmmmmmmmmm mmmmmmmmmmmm :||||:|||:|| mmnmmnmmmmun mmmmmmmmmmmn mmmmmmmmmmmm

mmp~ fowl [mN~ [mN;II

c. M =0 .90 Figure 27. Continued.

87

A E D C - T R - 7 8 - 4

SYM ~ • IReS i a % % % TEA CONF RIR. G 0.9 0 YES 0 0 0 0 1 I0 F-q & 0.9 0 YES -6 0 0 -6 1 II F-q v 0.9 0 YES -9 0 0 -9 1 12 F-q o 0.9 0 YES -12 0 0 -12 I 14 F-q

0 1

X p

-8

-12

-16

S0

5O

q0

30

20

10 A e

0

-10

-20

-30

. ' ~, J , I -' • . | I ' , ~ ~ .~ ! . ! ! '. I ! !

t-~! [ ~ \ 1 , , I t t i tt: : ! N " " !tr f 6 8 , i A • ~ o

-1! . . , : , ! i l . ' , " il.- I t ' : i i , t t ~; ,t , t , •

-qo

-50

-60 0

" ; - !

. . J ,

:--L

-V t , , , , . p .m . .

r- t - - I ; - 4

I . -

g 8 12 16 Zp

30

20

10 A t

0

-I0

-20

-30 -8 -q

c. Concluded Figure 27. Continued.

0 ~ 8 Tr

88

AE DC-TR-78-4

sYx I% • TAB5 aq l a % i~ TERCONF AIR. o I . I o YES 0 0 0 0 1 IO F-q A I . I 0 YES -6 0 0 -6 1 iN F-q V l . l 0 TES -9 0 0 -g I 12 f - q @ l . I 0 YES -12 0 0 - 1 2 I 14 F-ti

q

O:

-tl Xp

-8

-12

-16

6O

~H:llq:]1! ' ,:-IIl~I .o

i. ,o il~l:lii~ll!i~_ ill:Ill,-, ,o -i~t!-llHI). t i: l i!!i ~o ~H:tI:H-iI!!i: i ilHim ,.,o

- I 0

-6O

-20 Tp ~ ,,,,u1,,,,, , , [nnm,m

| [ l | l l i i l l l ) IN I | l ] [ l i l i l i

J a ~ , l l l l l l l S i I l l l Z I o~.,.,,,,,,,j i~l+F~ l i l l l l l ) l l l !

" ' " ' " ' " " l ~ r + + i -~o _ ~ m i ~ i m i , u m , , i in

-50

30 mmimmmmmmmmmmmnmmmmm immmnmmmmmmmimmmmmmm mmmmmmmmmmmmmmmmmmmm mmmmmmmmmmmmmmmmmmmm mmmmmmmmmmmmmmmmmmmm 20

16

12 Ze

8

0

4.--I-

4-4-

,4--4-

.4--I-

-4--(-

.¢-.,I, -4-I.

-I-4, .4.-4.

LI "-+ -¢---m- ~..¢.

-4--I.

0 -'" 0 0.2 O.q 0.6 0.8 1.0

2O nmunmnuuummmmmunmumn uunumnnmnmmunnuuuumn

lO nnminnnnnnnuuununuun ummmnmJnnmnnmmnmmunn

A t unmnnmnmnnmmummnnmnn unmnnmumuumunumunmun ~zmmumnummmmuuunumun

° : i | | | | | | | | | l l | | | | | | l | i i l l i l l l l i l l i l i l l l l l

-~0 i n n n u u a n i l U l U i n i n i n n l i m n n e i l l m l i l l n l U i n i I l l l l i l l i l l l i l l i l l l i I I I I l l l l i i l i i l i i l l l l

- ~ 0 n l n n i l i l i i l l i l l i U i l i mmmmmmmlmmmlmlmmmmmm mmmmmmmmmmmmmmmmmmmm mmmmmmmmmmmmmmmmmmmm

-)0 ammmmmmmmmmmmmmmmmmm

0 0.2 0.~ 0 . 6 0 . 8 1.0

d. M . = 1.10 Figure 27. Continued.

89

AE DC-TR-78-4

SYM H., • TRBS s t 6 a 0,l 14, TER CONF Rift. O 1.1 0 YES 0 0 0 O I IO F-q ,~ l . l 0 YES -6 0 0 -6 1 t l F-q v 1.1 0 YES -9 0 0 -9 1 t2 F-q O !.1 0 YES -12 0 0 - 1 2 | 14 F-q

°Tt-ti!tH!Itt!I! ~ - ; :.-: -;

• . . , 1 "

2 !

_-,~ I!~t:tiLH tiiii i I:: .- . • '. 60

5O

4O

30

20

]0

0

-tO

-20

-30

-40

-50

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, - d ,

~-!-.1 ~-!-4- I-1

, l ' f

~-~ - .~ .

I ~ . . D

-- , t , - -4--

~.i .L ~'t . . . .

~_~ .&. I ! I

i i :

~---I - . 4 - -

[-1 - ~ - -

I-'i -C-

4 8 12 16 Zp

30

20

I0 At

0

- I 0

-20

-30 -8 -4

d, Concluded Figure 27, Concluded,

4 Tp

90

A E D C - T R - 7 8 - 4

SYM H,,, = TABS ~, ~a w 0.5 Y TES -9 0 @ 0.5 l; TES -12 0

~ TER CONF ~IR. 0 -9 2 3 F-q 0 -12 2 q F-q

¸ .I .. ~.

~ i l ~ - I I l l l - I

~ ! l ! l ! l i ! , L~i i ! i t ; : i : I , I I . L :

" ~ ! I ' I "

Ye lllllI[l' II ~: llllfll

l;llIl!ll IIIII',I I IllllI_il, Ili , l "

n'IlllllTll ~ ~ , , , , , , , ,

_q H-I-H-H-H-: :

6 01 ....

50 '~ ..... I"!, 1"1"

t"4 I

;00 t '~- ' |" -'t "~ I -*--4""Do I T'tT!

20 '-T .t !

z~e !0 ; i.:._i

o ~ -I0 M-, I

-20 MT!

-30 TTT! ÷ ~-(.

-qo !TFt

- 6 0 ;i!ii

a0 ;; ; ; ;

i iiii 12 " .... zf, H !! "-r

e : j j j ! J

o 1-I"

0 0.20.

Figure 28.

30

;if l i i i i i L I I " I I I I I 1 ' ~ I I i I I I I I p l ' " I I I I I A ' I !! • ! !,~" !

.M.T ~2-ii '-~-- - ~ - 1 - q-FHHH- ,-H-H+H-

q 0.6 0.8 1 .0

At l

-I0 i -20

-30 0

:llIIlll~,IIIII,:I InIIIlllIIIIIIllll llllllllIIIIIIIllll lllllllllllllllII lllllllllllP~mIIIl llllllnIl~illIP~: III IIII ~ill Ir.~IIll:

IlP~dIpl~dIllnIlIl ,~-~Imlmlllmlii IIIIIIIIIIIIIIIII lllIIlllIIIIIIlll IllIIIlllIIIIllll IIIIlllllllIIllll IIIllllllllIIIllll IIIllllllllllllll IIIIIIIIIIIIIIIII llllIIIIIIIIIIIIl llllllIllIIllIIII IIIIIIIIIIIIIIIII IIIIIIIIIIIIIIIII IIIIIIIIIIIIIIIII

0.20 .q 0.6 0.8 1.0 L t,

a. M = 0.50 Wind tunnel separation trajectories of the M V B from the No. 2 TER station of the F-4C aircraft, two fins canted.

91

A EDC-TR-78-4

8"LM ~ • TRB'S it ~ ~ % TER CONF RIR. 0.7 2 'rES -9 0 0 -9 2 3 F-ti

@ 0,7 2 TES -12 0 0 - 1 2 2 q F-it

0'

-q Xp

-8

-12

-16

IU "

fllHHHgI IgIIHni ,MIIHII

~ll|llll[llllll!lllll. l Tp I l l l l l l ~ l l | l i l ; l l l ~ , ~ u

I I I l I I I ; I ] ! T I I l l / ~ I ~ L l l l l ; l : l ! . . l : ' , ! l ~ l : l

• , : 1 1 1 ] 1 1 1

U IIIIIII!I lJ!l;lllll _~ ~ iiii!iII!!I:!|II[II

20

16

12 Zp

8

u;

0

I l l l l l l l l l I l I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I imlUnlllllIi IIIIIIIIIIIFAI I I I I I I H H ~ I I I I I I H I I I ~ I I ~ IHHIIP~IIII iiIimi~.,II III lllll~Illll

I I I I ~ I ~ I l I I I I I P ] IIII II llll,,,,

F~IIUIIlIIII IIIIHIIIIII IIIIIIIIIIII I I I I I I I I I I I

0 0 .2 0 .~ 0 .6 0 .8 I .O

30

20

. I °

60 ~-;-;-; ; -;4.-;-;-;-;4 .L '4",,-,#-(."4 P .I. +-', l '--t '-4-',)--#. - -+"

I A

I V ~ -e - i - ~ • l . t ~ -4 i 4--e - t 4--4 ITS - - t ~ ~ 4 I ' t ' - 4 - " . • • • • • e ~'-4--~ I - ' I - -O 4 -

/

110 : : : : : : : : : : : A

• e i t - e Q e t 4 i i e ~ - o 4 l • e ! e t t i e - t t "

4 t . l - t 4 l ' t t - t - I 4 - # t "

/

~ k I-l-I I t ~ • 1 I 4- ~1, 4-.,i--e-i i 1.4 e • • i .i ~

I - ! • I-~4-11 I I ~.. Q - • . .

: : : : : ." : : : : : : :

4 - P f ~ ' ! i - t ~ - t ~-i i , .~ . i i 4 i i i-e i-4~ t - .4 p ( . I - ( . * e4 - - O,

Z : : : " 22 " : 2 -~ I I I 4 l~--(~--+-l-@l )~. e. .+ i ,.i,- 4 i . + , - i . - i - • -÷ -4

i t , - ! 4

!

"I"4-- I l i -+-t- -i -i-i

- '20 '!"t ! :! !TT:!T! ""

. T : ! ! ! . . . . . . q -t-.r!T! L-:.,~--EI:ITI -t

- 0 "V-,'M'-r" VTl-t-r-V-1 .~i-; . ;-~ , ! ! ! ! ! ! ! ! , - t - - , i - t - : : : : -. : : ; : ; :

- S O T r i i i i i i ! i i i ,,ii • - . , i - . t - i , - . i - : : : : : : : : [ I

160 [ ' - l - r ; t T ' "1"1-1"-1-1 i : [ i

f I I I I 1 ! 11 J i l l I 1 : 1 1 1 I I I i I I ! 1 I

i i i i i 1

~ ..1L,4,,.| | I .-4q ! ! ! !

. i i i i i i " I 1 I I I 1

I l l l J I l l l i l

-10 . . . . . . . . . . : : : : : : : : ; - :

i : : : : ; : : : :

M"M'I-t- i

-30 i i i i i i i i i i i i ~- 0 0 . 2 0 . q 0 .6 0 .8 l .O

I

10 A t

i i 0 :


92

A E DC-T R-78-4

SYeA ~ = TABS ~s 0.9 0 YES -9 0.9 0 YES -12

~a ~ ~ TER CONF RIR. 0 0 -9 2 3 F-W 0 0 - I ~ 2 q F-q

W

O:

Xe -8

-16

. , , ~ , ":" ~1" ;~,"

--;-14 . ,~ . . ~ i i ; ; I ] I - ; i ' ' ' T ' : ' ~ ' " r() • ~, ,} i ~I~i:., , : : \_.:. ! . , , i':', N i - ' ; . ' . ' : i . i .

:j~! : I : .... = ,,.~ i~' I h )! ' ' ' 1 ' ' ' ~ i "

¥e I " I I ! ! ! l I N I I I I

q [ ),Im [ ',, i I _ L ~ - I _ ~ o q l H ' ' L , " ~ f ' t , + l + ~ i

. . ; , . .

~ ' ~ ~ b ~ : l l ~ l .~ I-l-t-ll-l-~rl r t I ~. , t r r r )

6 0 ~)~ ~ I ~ ) ] ~' ~ ~ ~ m ~ t l

q 0 I " " l! i i I ~ I I ' ~ + " , ).,¢m

, - ~ - ?

llm. I)m.I,

i i) 2o ' i)l )~l (')l ~-~-:

¢.- I . , O: r ..r~l

1 ' r * ,T " + ~ ,1"

- , - ° - " " ,~- ~ I ' -

it4i I i -F .v-! =l, i - i - i - I l i + ~ "m~ m~ --m]l~--il l + ) ~ ~=?-. I ! '~T l I ?I l ITI I ~ ~I"

i q 0 " - - I + - " I m~lr I t l ~ . - - t i t - " r ~ t

-47...: t , + ; - : 4 . . . . ~:- T÷4 ,.~. H . ,- ,q-r

20

16

12 Ze

I l l I N I l l ! I I I I . ' , ! l l i ~ " ( I I I I i l i i

. . . .

~ ,-~,F ~ , , , , _-

I~ 4 _ I ' [ 1 ! I l l 1.2: i I : i l

O OI ~ OI ~ OI 6 OI 8 ~ I 0

20 I+H-~÷~-H-,-FF-H+,~

I ' ; - ! o I -~+FH-HH+FH-t H+- -2o mTi - [ -~ H-H-H+F[H--~

0 0.20.q 0.6 0.8 1.0


93

A E D C -T R -78 -4

sYM ~ - TABS ~a l a % ~ TER CONF RIR. 1,1 0 YES -9 0 0 -9 2 3 F-~

• t , I 0 YES -12 0 0-12 2 q F-~

!J, ,

Xe : : : ., , -eli! ), t

• o , o , I

-12!!r::: ,-i. I. - t 6 m:-t- ',-I. i

L I I i I i i i i i ! E l "#'p m l l l m [ l l [ l l

/ I ) m m ! l m i [ l

t!:t-t i P t t i l l )

I l t t

I t t l liil

ItEt tti-I l i l t I t 1 !

mmm Nit

III

m

60

t!i I i- qO ) 1 ,o

I 20

)

0 q

-10

-20

-30

-m~O

-50

- 6 0

mmmmmummmmmm mmmmmlmmmmmmm

16

12 Zp

8

LI

0

20 " " I f " 1 I I I I I

" " I : " i ( I I I N ~-~ , , - - , , im i i ~

I I I I !! ,! H

T! ~-I T/T

o 0.2 o.~ o., o., 1.o

30

20

10 A t

0

- I 0

-20

mammmmmmnmm mmmmmmmmmmmm mmmmmmmmmmmm mmmmmmmmmmmm ,mmmmmmmmmmmm immmmmmmmmmmm imnmmmmmnmmam immuiHmmmmmm )mummmmmmmmmm )mmmmmmmmmmmm immmmmmmmmmmm mmmmmmmmmmmn immmmmmmmmmmm immmmmmmmnmm )mmmmmmmmmmmm )mmmmmmmmmmmm )mmmmmmmmmmmm immmmnmmmmmmm immmmmnmmmmmm immmmummimnm immmmmmmmmHm

- 3 0 immimmmmmmmli

0 0.2 0.~ 0.6 0.8 1.0

b. Concluded Figure 28. Concluded.

94

AE DC-TR-78-4

SYM 14, = TRB$ 5m 5z ~ ~ TEfl CONF Rlflo 0.5 4 YES -g 0 0 -9 3 3 F-4 0,5 4 YES -12 0 0 - 1 2 3 4 F-4

4

O

-4 Xe

-8

-12

-16

6O

~-'~-~itiI:tl~! !:HI!~t 50

. . . . . . . . . t..Iit~ 4o

. . . . . . . . . , ) ~ '

i~iH:l H:!--IfH ~i{ t!t:ti ,o l i t

l'p q i [ l i l l [ I l i l l l l l l i l l ! . . . . . . lllllllll]l : ; : : : : : :

Lilliiii I I~m~'J-LLLLI I T I I l I [ I I I ~ 0 : ~ ~ . _ = , , -4 l-i-i-l-M-t-r : 2 ! ' ~ ~

Z~ 10

O l

-10

-20

-30

-q0

-50

-60

i!i i ltl i l iti i i i Mll i l ! iM! lllHgliHltfl !littfllfgllli tfltnlifl!ntt

ttiilflflll!lU U, ih~iIUi.~ illiHttfi!l!i ilttliiilUim 'dtllilliil:) mmmmmmmmmmmmmmmml mmmmmmmmmmmmmmmmml mmmmmmmmmmmmmmmmml mmmmmmmmmmmmmmmmml

2O

16

12 .7p 8

4

IIIIi1111 IIII:IIII

II-I-I-T'+-I - I't

t:N_--t-.N:t ! t

i i

)-.¢-

t"t

0 0.2 0.q 0.6 0.8 1.0

3°', I I I I ' , I I I 14-;-;-;- -i--i-i.-i

III! 2 0 : ~ i i i ,,x, ])?! ivmv

10 -'-I-I-I-

01 -*'*'*'*-

-I0 . .TM-. F ~ T -+-4--q~: : : : :

: : : : : : : :

-20 . . . . . . . .

-30 i i i i i i i i

m_am

imlll

limnmi limiUl llmmmmi immmmi immmml inmmmml immmll immmmml immmmmml immmml lmmmmmml immmmmml Fmmmml llmmil immmll immll]

0 0.2 0.q 0.6 0.8 ] .0

+. L

a. M = 0.50 Figure 29. Wind tunnel separation trajectories of the MVB

from the No. 3 TER station of the F4C aircraft, two fins canted.

95

A EDC-TR-78-4

SYt~s H, = TRBS ~l ~ % ~ TER CONF AIR. T 0.7 2 TE5 -9 0 0 -9 3 3 F-tl

0.7 2 TE$ -12 0 0 - 1 2 3 q F-q

O"

Xe t t

-8 , i , r

-16 I;-

.1 .;J- ; 44- * - - ÷ . i - , l -

"T T't. '. I "~

i . , ' I !

:I N i , , : : . : : :

. , , t - : ! " ' ' l t t . . . . P ! I , , i

" ' *"' T'II " ~ ' t ! t

~e ~ i i i I I I ! [

°,e,, i _ ~ -

I I I I I I ! l I I l l

r..

2O

16

12 Ze

8

0

1 |

• | , i I

i l " !

I I " i

I 1

L -Li [-- ~4

0 . 2 0 . q 0 . 6 0 . 8

; l-[-J

! I*'! ~ | - ~ ,

i L ; , ~ o - $ .

L ; : " ~ ' d "

, , . O

I T ' "

I I I I I

I I I : I l l ' i ] ! ! i 1 J i l l I

I I I ! i i llliL~i~ -*I II I !II

l ; I I I-l-~-I ! ! ! ! . . . . .

1 -1 -~ 1 1 - I -~ t t l

~-L~. i -i-i4 -;-;---;

1.0

b. M== Figure 29.

60

50

qO

30

20

~ I 0

0

- I0

-20

-30

-qO

-50

-60

.|-1

i!

,ii I. 4 o l, 4

I--: e ~

¢ t - ' ;

1 -

I

I I I I I 1

3°I= 2o +

-10

-20 ii -30

0

H-H-..h L- H+H-I--

0 . 2 0 .

= 0.70 Continued.

. . . . . . . . 1:: I=, 4 - I - ~1 - I 4

I -P 'O~ I 4"-,

4 - - - I

?T! ! - I ! . . . . . * - ~ - 4 - 4 - 4 ~ , . . . . . . . ~-, T

iJ.i i.i i-. .~ : - ' : : ', ~: i ; ' ' , , - - I I 1 L ~-

~ . _

!H! : n

. . . . 4-

-i.-LLi., ', : " - 1 " . - i , ~ - 4 - J r

I i l l l l ' _ : I l l ! ! ~ ' f . 1 ] i i ~ L ] I "1 ! r'1~ [ !

! l l n

1 T ! T iJ. 1~-~- L-I. - -~-4 . . .4-4- ~ .~

1 1 1 1 - ['~

q 0 . 6 0 . 8 1 . 0

96

A E DC-TR-78-4

SYM H. = TRB5 ~t ~a ~ I~ TER CONF RIR. 0.9 0 TE5 -9 0 0 -g 3 3 F-q

e 0.9 0 XES -12 0 0 - 1 2 3 q F-q

o~ ~ ! ~ I , , _ _ ,' i t ~ '

Xp , . . . . . . , , . . :N ~. It - 8 - ~ • =_ . . i . , , l ~.~ !~. . . . . . : , : ~.~,~,~

"t: 1 ,~ - 1 2 ~ I ' : : ''~ ".-,"1

I ' ~ ' i . ; ; ~ : ~ , : ; i t ' ; " t i i ' - 1 6 .~ ~. : . , ~ i . ; ~,.

I t l l l l I I l I [ I L I I J L Tp LJ[ ~,!,l:J I : l l ] . [ . ~ ,~

0 I , i ' i ,, ~ - 1 4 ~

60

S0

q0

30

20

~ 1 0

O

-10

-20

-30

-q0

-50

-60

I t 1tt ti t-l-i-i t ~ !, : I-!-T~ t t ]-!-l-tt- i-I ' i i-I ~'- ,-. r t , t , . ..~

xi t.it.] i i ] i t ~-L i ! t t i h i t !! V F-

" "'" ' i l l" I t N - t !-1:

• i;i -,.. ,-; , + t-i+i-t_p-

. ~ - " 44- , ~L

:T t ' t , r3.t ' - f fH-~-~ • H-H4 ~-~ H+

; , . .

H

!;i i.!

,±

• ~ - , ' ,

H- .H-

.¢ i 1 :

20

16

12 Ze

I I I I | I I - I I I l l , , , , , , , , li_ ~ I | 1 1 I I I i l ! I I | | ! t 1 I I I I I I I I ! I 1 1 I I I I I I I I I I I I Y I 1

i , , , ' H+FFFJFH r i l l 1

0 0.2 0.u, 0.6 0.8 1.0

3o H+H+H- 20 -H-FH--I--,

A*IO

H - 1 o I + t - H + ~

-30

I l l ; I l l | . ; I [ I [ ! i I I I I ~ 1

H~ : -H~÷~t i+t+FFFHH H-tI ' . ' ' = ,H

I ' ~ t t i ~ , i i ! i |

H-H-t-nH--t-H t-t-H+Pr,m-I

0 0.2 0.q 0 .6 0.8 1.0

c. M= = 0.90 Figure 29. Cont inued.

97

A E D C - T R - 7 8 - 4

SY~I I% - TRBS (km ~a s) % TER CONF RIR. 1.! 0 YES -9 0 0 -9 3 3 F=q

O 1.1 0 TE5 -12 0 0 =12 3 q F-~

1t:I t : ; ' iit ~ ; . , ' . ; ~ ; i i

1"! ! . . . . i~ ; " Xp It-: t ~ , ' t " ' ' t ' ' ;

' _ * ' ' _ ' t ' ! ' ' _ * + " _

-e i) ~ ~ : z,; , ; :~. ;~ ~!" ' ! ~ . ! ' i , ! l ' , ! ' )

& ~ . • o]~ [.: iii i i ; ; '

-11

Yp 11 H__H_H~_H__HH_~tmH__ I

n . ~ ,-!-t-t~.J4-1-i-H-I-J-)-~-; ~ t

- I ~ r ' r - I - ' - [ ' i - ; - ' ' ' ' ~ ' ' ~ : I , I I I

so i t ' ; I ; l l : - ; H ; : " ' l:.,. -ii.', -'*" " . . . . ;-~-1. I ;

- - • ] I

t~, , 4 : , -" I - , . . . . . I F I 1- i: :it i qO : ; ; ! t "r t

rq-, --t-r- I ~ ,-- I+~ , ). )-, +++ - ~

.... 'T i'-T .LII,;: , ~ m ,

4 • , - - -

20 F! . . . . . F t - l t ; ; ; : ~ : : ~1-: : " ; ' I : 1 "

,o i i : :, i i : : , ; . A . ,-.,. ""~.,-~ :: - :~ l :q~ O' ½;" : ~" ""'T!"-rT

• ~ s F : : k k . - ~ i . . . -I0 ~T~ ~1: t-i-, f-Fl---). '~,

. . . . . . "~' ~ ! ~:~i -~ ',-t- ,.-44- : ~ ::t:! -~+: ~FFFT4T -20 ¢.:_i :: +*+

:.; ....... il~-~ -30 : - - v-r-V : " ' ~ '

. . . . . . . . . . . . . '-" , - ' - . - . H - ~ 4 . . . . . . "|:D.~ . i i : , i i

--+~H

......... l-i--i-lr -50 .... 1.

-60

Ze

20

16

12

8

0 0 0 . 2 O.t l 0 . 6 0 . 8 1 . 0

0 . . . . . . , , , , , , ,

0 ' " ~

-10 . . . . . .

- 2 0 . . . . . .

- 3 0 - t - ~ . " ~ - . -

i i l n l l l l I l i l l l q n m l m l m J

i nl iml~ ml l l l l~ lnnnn~

I l m l m l ]

n n m l m n m l nnummul nnnunu~ immmmmm~ mmmmmmr mmlmmmm l i l l e | | ~ , | | | I I mmmumm mmmmmm

0 0 . 2 0 . q 0 . 6 0 . 8 1 .0


98

A E D C - T R - 7 8 - 4

S~! I~ - TRB5 ~m ~ ~ ~ TEA CONF AIR. Q 0.5 q NONE - 1 2 - 1 2 - 1 2 - 1 2 I 5/5A F-q

0.5 ~ YES -12 0 0 -12 ! 14/14A F-~

"i" " " "~"(~,,NL t t'~ . .... )

X P L 2 . [ . . . i : m : : 1" 1: ',~-r,- .i.J.i.Li ,-,"ii.~..i-i , I - • l - l - - i i , - i i i , 4 I I - ~ i , , l - t ~

: r t - * f 1 ! - I ' 1 r? - I ' 1

"fp

, , , , , , , , , , , - H - H - H + H - {

60

50

qO

30

20

z~ lO

Ol

-10

-20

-30

-qo

-SO

-60

- I - . |4-L - . I , - ,IP-I,.- I,-

"r ! t t . . _- :

- + - . t - e - t .

-F!-F? -~ +-o- •,

-F t ! t --d~# -~ .¢-

-t l-hlz 4 14/I.- -4- • R-~ -

F_~_ i- • 41 I 1 ~

- , I - I I ,4.- .4--

7!!. ! -+ I - -P 4 - .

• -,,i,- ~. ,.I,--.I--

-!-. !TT

-FFFT

- l - l - i f -

LLL -!-~r --4- | --4F- I- .. q-= ~- ¢,-.~

-~ !T r "~P - o " ,P ~ -

-! rF r

-!-!~. F -1-1- 4 . . 4 -

-44-4-1-

"~t ~,'-

- + -~ - o - * -

! ! T ! - ?

,..' ~ ! H - I "

i i

4[ ii I !

- I - I -M-

T! .-rT

" M i i

20

12 Zp

8

Ll

0

)1)) )11! )))[ )i)) )))) ))))

) ) ! ) ( i i~ l l : : : : ; :

D : : : : : : ;

- ~ - L -LLLL J-l-~ -i-£-~$.

. . . . 4-4- - 1 J-Ll-

r t - l - r T - "~* -+-

0.2 O.tl 0.6 0.8

30

20

At lO

OI

- lO

-20

-30 .0 0

I I I I miw~ I lnum~ ,immml ~mmml immml immml lmmml lmmml inmmml InmUl llmmml

i i i i l immml tmuml immml immml immmml )lmnl immml ilmnm i i i i I I I I i i i i

0.2 0.~ 0 .6 0 .8 ] . 0

t t

a. M = 0.50 Figure 30. Wind tunnel separation trajectories of the MVB with

simulation of fins returned from -12 to 0 deg during the trajectory.

99

AE DC-TR-78-4

SYM H. = TRBS % ~ IS N . TEA C0NF AIR.

m 0 . 7 2 YES -12 0 0 - I Z I 14/14AF-tt

Li !111 '" , , ' , I I l i l ! ! l ; -

0 EliCit)It ! • . . 4 . . - 4 - , ~ m -

-q' ' ' ' : . la J-I Xp . . . . - 8 -F!-!...r .!-!;TT

-+-+-~-i- - -F -~ - -o - - e -

- - + - t - -H - - 4 - ' + + - i -

- 1 2 : : : : . . . . ~ m t mlmlmm t 4 + O --

- 16 .-r-r-l-i- --r-l--~-

immllml i i i m m l l U l n l l mmmmmm

ii!ii )11151 i l i i i l i l i ~ l l l i i l

!lll!l

T-H+T-H-k~H+H-H

: : : ; I l i

5 0 i i i i : : : • . . : " :

: : .- : : : :

I~0 -l-t-t ' l- - * -~ - l - i . - i . - ,P,- .,,,,4-.-e-t,,

30 -I"I-1-1- - - ~ t - - ~ -~ - - - - 4 -4 -P

- 4 - : : : ; - I - + ,

2 0 - r - r r r . . . . . . . . . . . : : : , - 4 - ~ -# -4 - - - 4 -1 -~

- - 4 -4~ -e- - - t - " ~ l ' - k

. . . . - l - l - r A * x° : : : : + H . . - t - P . . ,P , - . i -

o,

-1o T~r ... - ¢= i - ~= ( . - - - l - - . i - - l -

- - 4 - ~ 4 - . - ' 4 - I " - k

- 2 0 - l i t t - t - in ~ , - o - ! - 4 - . 4 - - - 4 ~

: : : : : : :

_L _i i i ' - q O :: : : : i

. . . . ! ! ! H A

- ~ U : : : : ; ; ; . . . . i i i

I I I

- 6 0 -~ i i i I n ,

2o Ell,,

ml . 12 mi L ml

°½|

ii,m=,mi'--,'rj .iiii mmmmmmmmmm immmr~ mmmmmmmmmm inmw~ mummnmmmm in.win mmmmmmnmm imvJm mmmmmnlNmn ~m~mm mmmmmmmmmm wmmm mmmammmmmm Immm mmmmmmmnu ummm t i n m i IP I l l¢ l l m | l [ ] ~ | ' | . ,

• In i N mnmmmr~ammm immmm mmmmp'~umm| )mmmm !ii)~ mi m ) mmm , i | ihil= ih:: u~m~moPl~oN;m

mmmm

0

30

20

At I0

0 _,o! - 2 0

- 3 0

l =. = ." = l .m ." ". ." m. =. .m _" = ." .= ." I l i l o m m a m n n n l u m m m n n n • I m m m m m m m N i m i i g i n m i

N m n m n N m m i i n N m m u n i i I N N n N m l N N m N n N N U l in l U l i m i i m u i n = m n n m n i i m li, m mmln nnm m:mm m mare,rim m i Imnmunumm,mmmmnumN INmNNN mmmmnmunmmmmmmi um.q~m~m p~mnnmun num~, l I m m l l l l l l l l n l u i n n l i H i l i l l i a H m m a l n a i l i m n u l m l u m n u i n i m n m a i l u m n a u u n m l n u n n n n u n n N I n m n m m m m m l m n m n m m N I l a m m l m m m m m m a e o u m i i l i a l l i l i l m m i a l i l l i l i i l l l l l i l i m i l a n n i i mmmmmmmmmmlmmimmmmi mmmmmmmmmmmmmmmmmmm mmmmmmmmmmmmmmmmmmm

b. M= = 0 . 7 0

F igu re 30 . C o n t i n u e d .

100

AE DC-TR-78-4

SYld !% = TROS I t Ib a Is I~ TER CONF AIR. 0 0 .9 0 N O N E - 1 2 - 1 2 - 1 2 - 1 2 ! 5/5A F-q m 0 .9 0 TE5 o12 0 0 - | 2 I 14/14A F-q

- i ~- I

O: ~_ . - i -

.q -I" . | -

XF

-o ,.t ,"4-

- 1 2 -!"

-16 [:

Tp

I.LL

[ [ I :

- . _ : : .

] l ~ 1 l N - I - 1.t 1- • -

. I -L- I . .

? t l

• l

1 ' 1 I I ' t

1 . 1 . i -

: 1 " !

i * - ~ - I |

I l l [ l l ! l ! l l l ] l | ! l : i 1 ! I I 1 I l l . . ] . _ ~ - ~ . i . . ~ . ~

~ l ~ V i ' l . . . . . _ - - - ~ l i i l l i i l | l l l i l l l

H. PH +H, , H+t _ ~ I I I I I I I 1 ~ 1 1 1 1 1 1 1 1 1 1

60

50

qo

30

20

10 ~ l O - 4 -

o

-10 !

-20 _%

-311 i -qC

-5C

-6G

20

16

12 Zr

: !!! . . . . . . I I I I i i ! ! i i , ! ! ! I . . : : I V • I / , i i i i i : i I / l _ . : :

8 : ilA" . . . . .

i l l l l l q ~i . . . . . . ,., i i i i i ' 0 . . . . . I I I . . . .

0 0.2 0.q 0.6 0.8 ! .0

30

A$ I0

2O

01

-10

-20 I

-30 0 0 . 2 0 . q 0 .6 0.8 1.0

c. M= = 0.90 Figure 30. Continued.

101

AE DC-TR-78-4

SYld 14, = TABS I~ I ~ I s t a ?ER CONF A IR ,

• I . I 0 N O N [ - | 2 - 1 2 - 1 2 - 1 2 ! 5 / 5A F-q

,+i-m-r-i- 7.1:: :

I U ...... :i " " l"i I t l . ~ ~-;-.;-; L-; ( l-.J, I ~,4 ~. 1

16 ~; ;~; -; l-l-Ill :~,

Ym' q '- • ;

6O

50

q0

30

20

~ 1 0

0(

-10

-20

-30

-q0

-50

-60

_ _i.-i..i-i. : ..t : ."

- - - 4 . " - } + 4 -

-T.r!-: l - - - - 4 - a - - 4 - 4 - -

-- , - 4 - 4 - - 4 - . ~ - - -4-- | - 4 - 4 - -

. .£ i . i .L

' - I ! -TF -~ - 4- -o "t'--m¢'"

--' "'4~| "4'--'4--"

" - t ' l l " t" - - 4 - - | - @ - 4 - -

. " 4 - - e - - ~ - ' 4 - -

- 4 - - . - 4 - 4 " -

- I-.L&;.

"'H "4Mii ' " lk 4 '~

,,~ ,.,,.1-- m.,-(.- , , I --

-"T !TT- -,.+- =--(,.- .e--

- .T-!-T-.~ -1 , , - I , - - ~,- 4 , , -

&HJ..

! i i i

20

16

12 Zp

8

q

0

llil II III II mmllll a w r - ~ !

: . " : : ." :

: : : : : : : ; : : : : I : : : . : : ' " i ! - 444

. - , m , - i - . - 4 - ~ .¢..- e-

+ - o -

0 0 .2 0.q 0 .6 0 .8 1.0

3O !!i!

ZO . . . .

- ~ l - I ' t &¢lO . . . .

-!o -+-~.-

-20 i i i i i ionmmmmmmm i . . . . lwmmmmmmmmm

-)0 "iF-~JF'~ immmmmmmmmm immmmmmmmmm

0 0 . 2 0 . q 0 . 6 0 . 8 1.0

mmmmmmmmmm ammmm~mmmmmmm immmmmmmmmmmm immmmmmmmmmm mmmmmmmmmmm mmmmmmmmmm mmmmmmmmmm mmmmmmmum mmmmmmmmmmm mmmmmmmmmm mmmmmmmmmm ~m=_ mmmmmam )~nmmmmmm :Jmmamumimm ' , l lH|I=,'=I inmmHimmmmi Immmmmmmmmm immimmmmmmm iummmmmmmm


102

A EDC-TR-78-4

k l . o TABS 81 8~2 0.50 4 YES -12 0

b J

83 ~4 0 -12

TER CONF I 14/14A

5~ ~ ' - ' / / - - 1 f "

I - I 0 Xpoft

FIN RETURN MECHANISM ACTIVATED = 1.5 ft.

I0

Ep,ft

j

Figure 31. a. M® = 0.50

Illustration of MVB trajectories with simulation of fins returned from -12 to-O deg cant.

103

AE DC-TR-78-4

M= ~ TABS 81 82 8 3 84 TER CONF 0 . 9 0 0 YES - ,2 0 0 -12 I 14114A

"~ - 5 - I 0 Xp , f t i I

C'"~'"r~-'~"= ....~5~'._ J E = 1.5 ft

I0

t p ,ft

s - "

. . . . . . . . . . . . z:C_J

b. M =0.90 Figure 31. Concluded.

104

AE DC-TR-78-4

0 .9 2 NONE-12 - ! 37 R-70 0.9 2 'rES -12 0 0 - 1 2 I 3e 1:I-7D

V 0 .9 2 NONE 0 0 0 I 39 R-TO

It

O,

Xe -zl

-8

-12

-16

I l l l I l l i t l l i t I

m ] l l l l l i i l l l l l l l l l i i i I I I I I I I 1 1 1 1 1 1 1 1 1 1 1 1 1 1 | I I I I I I i l 1 1 ! 1 1 1 1 1 1 1 1 1 1

~ z _ ! i i l I I ~ , im I I l l | i l l ~ r - P * i l l l l l l l l l ! l l l l l l l

lllIlli!llllllllllI[ I IIIIIIIiI!I!IIIIIIIIl

I ~ l l i l l ! l l l l l l l ! l l l l l l l

20

16

t2 Ze

8

60

50

tlO

30

20

~e lO

OI

-10

-20

-30

-qO

-50

-60

• -i.-I....;- I . ,

- - " 9 -

- r ' l ' t ' t " -i- # - t - 4, . . , , . 4 -# ..t-..i.,,.-

• t ' I T ~

Frl'l '

BI:I: Ill,If IEII ili

iBiiii I l" .iiufi ~ I I I I I a J IIHIIi

i!ii i! IIIIII1l • •

IIIIIII~ llllllll Illlllll IIIIIIlll

I mmmmIIl !lImmIl ImmmII IIInII II'

0 O,

Iilml IHmmmmimB l lmml ImmHmnmmm lmmm( mmmmmmmmm mmm~--ammmmm.mmm zmmmmmmmmmmimmmm

lllIIIII::IIlI IIImlmmmNmIIIII INIIIIIIIIIINI iiimmmmmmmmimiim' ilmmIimmmlilllil IlllIIllllllllll IIIIIIIIIllllllll IIIIIIIIIIHIIIIII mllllllllllllll ~IIIIIIIIIIIIII

iiiii!iiiiiifii!l

30 ~

20 :::

A ,10 !i!. . i i ! " ! ! )

0.2 0 . ; 0 .6 0 .8 1.0

a. TER station No. 1 Figure 32. Wind tunnel separation trajectories of the MVB

from the A7-D aircraft at M = 0.90.

I05

A EDC-TR-78-4

=SYM I~, e TR9$ I i li~ t I It i ?ER CONF AIR. e 0 . 9 2 NONE-12 0 O -12 2 4 0 A-'/D i 0 . 9 2 YES -12 0 0 -12 2 41 R-70 v 0 . 9 2 NONE 0 0 0 0 2 4 2 R-70

.i Xe -9

! i l l t glilH Him igllfl lglgt

¥e H+t+4-H-t+H-t+H-I-H+I I l l l l l l l l [ l | l l l l l l i l l

o ~ I I I i [ I [ I [ [ I I I I [ [ [ [ l l l l l ! l l l l l l l l l l l l l

_~ H-t+~i-H4-H-H+t+, H-I

,o i !:

20

Ae lo

O~ "! r ! , ~ - -. --i- 14-1-

-10 ' ] ! I T

-20 . . . . - i - -~ | I I -

-30 "TTH- - - .-,iP 1...-4-4,,-

--1- I - M - - l t O . . . .

-so -T- -r!T

-60 : l i t

Ze

20

16

12

8

q

0 0

IIIIllllll IIIIIIIIII IIIIIIIIII mlHllnmnmu I I I i I I I l l I I I i l l I I I I I I I I I l I i l l I I l l I I I I I I

i J f i i i - I n l l U l llllliIlll IIHIIIIHIIII

l lIllIIIII IIIIIIIII mummlmnmil II~llllllI

30[ ,,!, ~,,[ • " " 1 1 1 ~

I :=:¢: J i l l

2o i : : : : ,,,,,,,, : : : ; I l l i i i l I I I I

I0 ~ 7 : ! ! ! ! : : : : : : : :

O: - i ~ i i i i . . . .

.10 .. i i i i i i i l i : ~ : I I I I

• 2 0 , :~::':: I I I I I i i i i I 1 [ [ i " ' : " : I ~

'30 ~ i i i i I I I I 0 0.2 0 . ; 0 .6 0.8 1.0

b. TER station No. 2 Figure 32. Continued.

106

A E D C - T R - 7 8 - 4

SYM K. " TRB5 t a O 0.g 2 NONE-12 m 0.g 2 NONE-12 A 0.g 2 ¥(5 -12 v 0.g 2 NONE 0

- ~ 43 1:I-7D 0 0 -12 43 R-70

0 - 1 2 ~ 44 R-7D 0 0 0 4 5 A-70

x,

,re [i 01

-iS

i

60

50

q0

30

20

ae I0

1

-tO

-20

-30

-[10

-50

-60

.~L ~-

Zp

20

16

12

m n l l m U l i l l i n l l u i l l I l i l l U l U l I I H I I l l l l n l U i l i l l i l l l l l l l l I l l l l l l l l l I I I I B I B I I B I I I l l l I l l l l l l ~ B U l I I I I I I l l l l l l l l l I l l l l l l l l l I l l l l l l l l l I l l l l l l l l l

I I 1 1 1

: : : :

, . . . . . . . . . l i l l i i l l l l lummmmmmmm i l n l n i l l l l I l i l i i l l l l

01 _ _ I l l n l i n l m l

0 0 .2 0.q 0 .6 0 .8 1.0

3O

20

10 At

0,

-10

-20

-30 0

i I

i l imp iD InDigO I I I I I I I I I I B I l i l l I I I I I I I I I I I I I I I I B I I I I I I I B I I I I I l i l l i l l l l l I l l l l l l I I I I I I l l i l l I l e a l I I B i l I l l l l I I I I I I l l l l I I I I I I I I I I I I I I I I I I I I l i B E l I l i l H

N".ilo~lJ llolN,11lll:li Iq

c. TER station No. .3 Figure 32. Continued.

107

A E D C - T R - 7 8 4

SYM I'1. ,, TABS St

o . g 2 N O N E - 1 2 & o . g ~ TE$ - 1 2

I~ S s ill PTLON CONF AIR. 0 0 -12 6 29 A=7O 0 0 -12 6 24 R-T0

4

O:

-q Xe

- 8

-12

-16

Tp

20

16

Zp 12

8

q

0

~ - % l ? ~ t ~ .

"i i ~ ;.-I- " ' ,~.~ '

. ~1 -i.-. '-,- ' I ! ' : ' : :-I ; ,

. . . . . . . ~ . L ;~ :-|~ : : : : : : : :

~ * l . I f . . . . . t-: : : ' ; - , I "I ~" 1-t . . . .

q i , -

TIMI;IilIIIIIIII!Iil .q I - H - : - t - H - H + H - t ~

|IIIIIIIIII IIIIIUHIIII IIIIINIIIIII InlIIIIIIlIl iiiiiiillmlll IIIlllllllllI IHIIIIIHIII IIIIHIIHIH IHIHIilII II

I I I I I= l l=_I i l l Illllllp~IIII IIIilIIT~IIIII IIIIIITLIIIIll IIIII~.~TIHIII II • • I IIl.~l,llIIl,

I

0 0.2 0.4 0.6 0.8 1.0

0 . . . . . . . . . . . . . ~ , ,-4.--t-(-. t - t - i - t -4- # -# .~

- 4 - H - 4- #--e-# -4--~ ~--~

-1"-r-f-iT 1--~-1--t f'~

t -$l~-t I- !1.tI-4 qO ~ - ; ; ; - ;4 ;-.-;-..4

3 0 : " ' - r T ? ' t I • t '11~

~0 ~ : : : : : : : : : :

~e 10

O:

- t O

-..*- :Jr-

"5" |

4 - ~ , . i

-S - ~--

-4- ,

-20

-30

-40 ~

- 5 0 :

-60 "

q- - 9 - } - 4 - ( - - # t - , - t - 4 - # ~ - , -~ ~ , -

~-t±tt lLai.t: .4- ,r,r !~ !T! TTFT" -t- ~: . . . . . . . . . . L~.

-- t . -4--+-4--4- l - 4.--4--~-~- -~ '

~ -.~ l '.t '.t-fl-':.-I '- '-I- -I- '+- ~ - t - i - 4 - ~ - - ( - - e - 4 - ~ $ - - ~ -

. . . . . . . . . -I- .T-

-;- + r -M-I -M" ~ ' I - , I - _.

~?'~ii i i l i f . ~ . ~ . : : . : : : . +

I

20 j~ ~x" i i i 10 ' - I-,~l: ~, ,

0 : ~ i-~ii ! i ! !

-20 H-H- ~. ! i i i i i i i

- 30 . . . . . . . 0 0.2 0.~ 0.6

I I I i t

" i

0.81.0

d. Pylon station No. 6 Figure 32. Continued.

108

A EDC-TR-78-4

SYg If. = TABS Ik I ik i il l II i HER CONF AIR. • o.g 2 NONE-12 0 0 - 1 2 ! 25 fl-70

"o~t4.~~t)Hft~t~1 .o )t?4,.~l).~~l-fl)tfTtl-t~HI ,o

x, -"f!.tTttitl-rtltl.i.ttiH! ,o -"l-14+l-H:llllill:l-tll:i+l ,0 20

]',',, ,.,o OI

-10

-2O U l i i i l im I I I I-,i-i +p ~ , , , , , , , , , , I I I I I I I 1 1 I m I I I I 1 1 1 i i I " 3 0

I l i l l l l l l l ] [ , - ~ 0 _ ~ , , , , , , , , , - l l l l l l , -50

-60

30

20 20

Zp

l i i l l = l l l l l l l l l i l i i = mmmmmmmmmmmmmlllmmll mmmmmmmmmmmmmmmmmmmm mmmmmmmimmmmmmmmmmmm mmmmmmmmmmmmmmmmmmmm mmmmmmmmmmmmmmmmmmmm

|i||i||||||i!||||!|| I II~IIIIIIIIIIIIIIII ~iIIIIIIIImIIIIIII

11111111111111111111 I m i l m m B m l l m m m I m l l l l m | l B M I m g m m l m m m m m l l l l | inmlmmIlmlmmmmmmmmmI mmmmmmmmmmmmmmmmmmmm mmmmmmmmmmmmmmmmmmmm mmmmmmmmmmmmmmmmmmmm

l l l i l l l l l i l i l i l i l i l | immmmimmmmmmimmImlmI mmmmmimmmmmmmIImmmmI

16 At !0

12 0

8 -10

Ll -20

0 -30 0 0 . 2 0 . q 0 .6 0 .8 1.0 0 0 .2 0 . ; 0 .6 0 .8 l .O

t

e. M ER stat ion No. 1 Figure 32. Cont inued.

109

A E D C - T R - 7 8 4

• 0.9 2 NONE-12 0 0 -12 2 27 R-?0 A 0.9 2 'IrEs -12 0 0 -12 2 28 R-70

iiiii ; x,::li i i li iHi :::: : : :11.1-111:1:.

-16 -t rt.-r i M-

Yp q ~ 0 T P ' r l I 1 1 1 I I I 1 1 I I I I r I I I

u u u l m n J n n l u l l u u u [ u l l I I I I T I I I I I I I I I I I I I L I I I

. ~ l l l l l l l [ l l l l l l l l l / l l l

20

16

12 Ze

8

q

i i l m I l I I . . . .

" " i i i i " ' " ! ! ! ! . . . . i - i n : : : : .. : . . l l l l

l i n e

i l l i i i i i " ' " • . , I l l l I I 1 I l o l l

I rl ; ; - I - t - I - I - l i m B

l i M B - t - I - - i - + - I l l l

' " ; ! : : : : l i a r

l l i i : i i i i " " . . . minim

l u l l I I I 1 : ~ l l l l I m l l l l n

i i i I l i a i l l in I 1 I I I I l U l I 0

0 0 . 2 0 . q 0.6 0.8 1.0

60 .~_;_;. ~ ,

so T ~ F -4-.,D--t- • •

e - ~ t e .

3o ql,.-I,--4- | -

"1-t I - I - 20 . . . .

~ 1 0 i i i i [ [ . n !

i [ i i

- I 0 : : - :

_20 r t - t - r

-30 .TT. r r

-qo .-~..r- - : : : :

- 6 0 i i i i

jnii:q|u I I : l | | : , | ;

iiiiNtili iP.i!IKii I f iP. . i | | l i | | t ! | i i l i m i l l n n i l m m , IminmHmnmmm nnnunmummam~ l u i n H m i i i ~ in mR l i n e n mini

l|||-=-lUUU,, i i m m N n a m u l

:ran:.::| I | | | 1 = | , | , , imnmummmmml l u u n u n m n n n ~ I M I U B I n B I B O I imnmn m m m nnnml l u l l nngtmm mmml I m m n n m n n m l lmmann ilmmm mini I ~ m ~ i u n i i l U l l l i m i m m m l Immnm nnmmllmml ira.gram ii, n i u mmmml Iminml ~ i n nnnnil mmlmmluimmmn luHim mmmmmmn mmml i lmmmnmlu nnnl mmmmmmmmmmmmml

30

20

i0, A t

0t

-10

-20

-30 0 0.2 0.~ 0.6 0.8 l.O

f. MER station No. 2 Figure 32. Continued.

llO

A E D C - T R - 7 8 - 4

s~4 K, - TABS 11 ~ % ~ NER CONF AIR. • O.g 2 NONE-12 0 0 - 1 2 3 30 A-70

q

Oq

Xe -~ -8

-12

-16

Ye

20

16

Zp 12

8

0

immmmi! I" | | | ! I I

iiii Immmmm :ii

iiiiiii) llHllW iMiil IBm

H 4 . h u v p ~ ~ ^ ~ - H + H - F H

_~ H-)-H-)+H+~H-I+FH+I

60 _i-~.~-~w-

~ 0 : : : : : : : : : : : - + - o - I • + - ~ - I -+ - - 1 4 - + - l -

qO !!~ t T. t l . ! ! _ l t ...,m-t- .( ,-m- ¢- 4 + - - t - t - - P - - l -

30 -rt-! tT l-t--+.-t-P+- . . . . . . . . . . . - o l - ( - ¢ ÷ l + , - ! • ~ + -

. . . . . . . . till" 20 .i i.,i.i_~ii._+ )~.~.

z~e I 0 - t - t ~ - t + l - t - - r t - l - t - - ' ~ - 1 - 4 -4 - -1 - I - -+- - " - I - 4 - -4 - -4 . - - - 4 - I - ~ - . ~ - - 1 - 4 . - + - " - ~ - t - 4 - - + -

O( - ) ' l ' l ' t ~ l - t " ~ - ) t t-

-20 . . . . . . . :: :

-SO -F .t!-V ! t-i. + ! ) Tt-!-r tm--t i + i . . 1 . + , : I l l l I l i

. . . . I l l l - ~ 0 . . . . . . . , t - r -rr m - - t - ~ -

.-;--;- . ;-;- i-i-- .4 . . . .

-s0 _i-i,.~ ~__i_i_i_i_ , m : : : : : : " : ;

: : : ; : : : : * * :

-60 . . . . . . . . . .

mimmmil imummmi ImmmmI imimIII ii~IIi lmomIi lmmmIml lmmmmii immmmml mmmmmml I I I I I I I • • ,l.llml ilmlmmi mmmumi l!il I

l l l l l l I l l IIIlmmmIl lmummmml ,mmlmmmmmm mmmmmmmml inlmmmllmm inmmImImII iiimmmmmmm immmmmmmmi imnmmmmmml immmmmmml lllmmmlmIl illmmiilmi iiimiiiiii iiiiiiiiii iiiiiiiiiii lnII~mmmI immilliii mmmmmmlmm

0 0 .2 0.11 0.6 0.8 1.0

30

20

At 10

O,

- 1 0

-20

-30 0

l | | l l l l I B I B B B | lmmmmmmm immmmmmi immmmmmm immnmmmm immmmmmm ImmmmmIm immmmmmm immmmmmm immmmmmm rmmmmmmm )mmmmmmm imlmmmmm immmmmmm immmmmmm i i i i i i i i i i i i i i i i i l l l l l l l I I I I M I I I I I I I I I I I I .lll.I,

II~ 1111 11

÷I , , l i I I I I

I N I ; ,*! 11 II II II

4_ I ,111 IIII i IIII I l l l

- - ' ~ J C

I 1 1 1 I I 1 1 " I ! 1 1

4;H- 0 .20 .U , 0 .6 0 .8 ! . 0

g. MER station No. 3 Figure 32. Continued.

Ill

A E D C - T R - 7 8 - 4

~YM ~ -' TI~S 8! I~ I I I~ FEn CONF n l n .

e o . 9 E N O N E - 1 2 0 0 - I E q 31 FI- ' /0 A 0 . 9 2 Y E S - 1 2 0 0 - 1 2 q 3 2 R-TO

"oU l t tltt i i !1t t tl ,lTt -t.t)i ,FFl t+! f l lil !t:,! i, ft t( :tt-li ftit !

l J i ' ~ l k ; l l [ l ~ l l l l l l l [ l l 0 " ~ , _ m _ E ~ [ ; l l l l l l l l l |

I I I l i l l l l ~ l l l l l i l l l l l

_~ ~ + ~ ~ _ + ~ + H

0 . . . . . . . .

- J . e • |

50 r! ??) _r? ? -?-I.-T_t ),-4-," e - I - # • - 8 -4 - (k- -- O,'q)- "('--6,-

qO . . . . . . . . . . . t-n I-T 2 : : : : : : : . . . . ~..-I--!- m-+-. ¢- e -e - - t,-m- + -e ,

. . . . . . . . . . t'l r l - 30 LLi-ii i i4_ " :

EO . . . . . . . . . . . )-m ~ . ; : : : : " : : . . . .

~'I I-L: ,',:.; . . . . . . Od : : : : : : : - ~-Lid.- i - ( , - e - i - + - - I . # i 4 -

. . . . F t~ ~ : r ~ i , e . e -o -e= i .

- 1 0 : : : : : ; ; ; ; . . . . . -I." -t-I . , - , - + - , . P.-i. ,i.- e - p - • i - 4 - | - - e - I - -¢-,,¢--

-¢~0 l-I-t-| T . . . . ~ - "l-t I-~ : : : : : ; : : : : : : ~ -4 - - t - - # - I - - , - i - e -+ = : : :

A ~ -~u : : : : : : : : : : : : ) 4 . ~ e . m - - - i - - i ~ - - ~ . ¢ - 4 -4 - -

- ~ . 4 = ' . + . . . 4 - - -qo F-Ft:t--t: :g-l: " " - " "

. . . . : i i i i -50 r-rrr-r. "-v-r. ~ ' , i

l . - t - - 4 , - o - , t - . : : : : : : : : : : : : : : : ; : ; ;

- 6 0 i i i i i i i i !!))

20

16

12 Ze

8

immmm Immmm I lmml imnml immml imnmm Immmn immi l limmm I l l l l I l l l l I l l l l m in im I l l l l m iN im

q immmm [ H i l l i l l l l I l l l l

0 mmlmm

0 0 .2 0 .q 0 .6 0 .8 1,0

3O

A t

I 1 1 ! i l m l l l : : : : tmmmmm : : : : I l l l l l

I l l l l l 20 i i i i = , , = =

: : : : l i m l n l I l l l l l - : : : :

] 0 : : : : llmmmm )mmmmm

)()) ,mmmmm Immlmm

0 . . . . ~ mmmnm ummmmm

. . . . Immmmm - 1 0 _..blj..l~r Immmmm tmmmmm

.... )mmmmm -" .A-r. ,"~- ;Immmm

- 2 0 1 '" - ' - ' - ' - Immmmm mmmmm : : : : mnmmm

- :::: mmmmm _ . . . _ . . + . + . Immmmm

- 3 0 . . . . , m u u 0 0 .2 0 .~ 0 . 6 0 .8 1.0

h. M E R station No. 4 Figure 32. Continued.

I 1 2

A E D C - T R - 7 8 ° 4

SYM I% = TABS Im ~ ~ ~ HER CONF RIR. o o.g 2 NONE-12 0 O-12 5 31 A-TO A 0,9 2 TES -12 0 0 - 1 2 5 54 R-7D

I~ I l l l l I I 111 " ' " ' " . , l l l l "~

0 X-H-H--r! 'H ' -H- i 'i x,- -.r! 4

-,o fH, ...... +li l . -T-I-!?::::!- :

I l l l l l [ l l l l ] l l l l i i l l l Tp i l l l l l l l l l i l l l l l l l l l l

l i i l i l l l i l i i l i l l l l l l l O ~ l l l T I l l l ~ k l i l l l l l l i l l

l l l i l ! l l l l ~ t i J I I I I I l i l l I I I 1 1 1 1 I I I ; ~ 1 1 1 1 1 1 1 1

_~ I [ [ i l l E I I ! l - P l l , l l l l ! l l

60 ;_~_ .~. ~_~, .-++.-~- -I-I-4-~- -t-P ~-o-

5 0 I-1-I-I- "t?1-t" -.i--i-+-+-, . . . . 1 J-J-i- - , . ~ - . ~ .

~o I t t -T :!:tt--1-: "-'-'-'--~-, . . . . . . . . : : : :

. . . . . . . . . . . . . . : T 2 ; : I : i , . , I , . 41--.,4, , - - f l I p .O

~ 0 i't-I-T" "tT I-r " + ' - ' "

I ( , , - , I - - I , , - - - ,,l,--,(, , I - - / / - - - + - - I - I - I ,

2 0 I t l - t - t l I t . . . . . . . . . . . . . : : : ..

. . . . . . " " " * - ~ , . M : I • i i-.-.i " t ' - t ' t - t - I +--b ~ . - t - - t i - ~ - . < -~ -~ - i

~ l O i i-LL .L.;i-i- ..LLi.. • -¢--~+- - i . . . - P , i . . - i . - ~ - i , - - . i , - , - t - .

' ~.-~*- "t .~ l-t/ ,~-t

. . . . . +i-H-, .... ¢f~l'i: ....

- l O i ~ ; , -k-l.L:. : : : • I - - i - q.-. l l ,

l-.:q::: - " • t - e • P - , P - ~ i -

20 -: t r : . . . . . . m . . . . . . . ; : ! !

• o,,i - i - - - - ~ -~ o-~ -~- t -~- i / /

F-G-F . . . . ~ x

• .i-+-..t.-.. - i - - t - - . - : - - ; I

- q O I 1 - 1 T -t-l" M Tm' -1 - IP4--1 - t - - - 4,-4--i--4,-- " - ~ F -~ ~ , _,,.~:: ; ; : :

1 I I

- 5 0 i i i i i i l - t - ' t - * - * ' 4 -

m-l-l-i- --i-.i.--i-i : I i l

_ 6 0 i i i i i i i i l i l i

20

16

12 Zl,

8

[t

0

! ! I I I I I I I I I I : : I I I I I I I I : : ; ! ; ' : : : : : ; : : ' . . ' " : : : : -

i i : ! ! ! i i i i i i

" i i i i , ~ i ! i i i i

i i I - l - M - I - . - I ~ - "

M--l-NMii i i i i ~ N i l i l . ' ' "

~ ! ! ! i i i ill

0 0.2 O. kl 0 .6 0.8 ! . 0

0 . . . . : : : : ! ! ! ! : ! I I

20ii!i I :~I- ! i l l " • - - - I I I . - i -

i i i i i i i i . . . . 10 . . . . : : : : !!ii

A t . . . . i i i i A i H - . . . . . . . . t ! ! . .

l i l i : : : : - ~ - - ; - ; - - L i - L L ,

- 1 0 , , , " ~_i4 / i. ! ! !l. I ,~t~.. - + ~ - + - , -

-20._~_~i i ; ; , . ~ i _ J - L L L : : : : : : : :

-30 . . . . . . . . . . . 0 0.2 0.11 0 .6 0 .8 1.0

i. MER station No. 5 Figure 32. Continued.

113

A E D C -T R -78-4

SYM I~ " TABS I n ~ ~ Iko HER CONF AIR.

• 0 . 9 2 NONE-12 0 O ' 1 2 6 3 5 n-70 ,L 0 . 9 2 Y E S - 1 2 0 0 - 1 2 6 36 R-70

q

"04

Xe "q , . ' 0

- 1 6

'i'm, m~

OA

-m¢

2O

16

12 Za,

8

0

i!lfliHHligl ! !num umim@gt lllBgimlli 1flllmglHI

mmmmmmmmmimalmmHmmma Imnmmmmmmmmmmmmmmmmnmm wmc=)-~)mmmmmmmmmmammmm mmmmmmwlmmmmmmmmmmammm mummmemmmmmmmmmmnmm mmmmemmnammmmmm

60

50

~0

30

20

Ao 10

0,

- 1 0

-20

-30

-q0

-50

-60

I B i i m B i B e | imn u n i i l i l I n n m n n n n l l inn innuumnn imn inmmmmnn imm immmmmnu I I m l i m l u m m n Ill inmnmmmm imm )mmmmmmm mm imnmmmm mm imnmimm iNN lmmgmmmm l|) immmmmmm

immmmmmm imm immmmmmm imm immBmml !)~ ,mmmnmmm

immmmmmn ,mm mmmmmmmm mm immmmmmm

0 0.2 0. I~ 0.6 0.8 1.0

. r . . _ 30 __~_~_ . - , - ~ -

20 - rT~T ~ t ~

AtlO : : : :

O~ - ~ - * ' - ! ! ~ ! : : : : : : : :

i i i i i i i i - 1 0 . . . . : : : : : : ; : : : : :

: : l l

- 2 0 i i i i : : ; ; - -P-4-@-4- : : : : ; : : :

- 3 0 i i i i i i i i

I I IN IN II I I I I I I I I I I I I IN II IN IN II IN IN II I I I I I I I I I I I I

0.2 0.~ 0.6 0.8 1.0

j. M ER station No. 6 Figure 32. Concluded.

1 1 4

A E D C - T R - 7 8 - 4

s~t ~ • TABS ~m ~z % % TER CONF RIR. z o 0 0.~18 ~ NONE 0 0 0 0 1 15 F-q 0.0z El 0,50 q NONE 0 0 0 0 I Is F-M 0,01 ~x 0,52 q NONE 0 0 0 0 I 15 F-q 0.01 • 0.50 4 NONE O O O O I 15 FLIGHT TEST

q

O:

-q Xe

-8

-12

-16

!Jl:ii i 'j.) ' it' . . . . ' - ' i , , " ! ! . "

t • ~ • o ? o I l-I [ ' " " : ' " , !_ ' ~ , ! t ' ' I '

t-l-i +;I , t i :-~.'t~!-. T ! I : L i l.)~.i~il;i:

i i :1 i , t , . : i . ! : I " f T r , t , ~ ,

I'~ m l I l l - ' - I : l ! l I I I [ I I

0 . . . . ] . , , , ~ l , l

~e !0

O I

-I0

-20

-30

-qO

-50

-60

,o

' t _'" 50 ~ : ; . ; , ; ~. . . . . . :I ! I ~ I i i

_1.1 i ; . ' I ' 1 30 : : : : . ;;

. . . . . . , . , :-i 1:7 2o ! - t ! t ' -!,'-

I . l - l l - ~ e l ' - " h i l t 'f " I ~ - - + , m +- 1" -'~

i -i) • t""

T ~ ! ' !

7 '-r~- -l- -,+ 1-

- " ~ " " I '

. . . . L-- - t ' t .'-' 4 t - ~

. . . . I i

. . . . ' ] :-T- . - . , . -

:I:I:I-i:- ~ T -iJ,-i-t-. ~. l i -lq:i-i- -i- : )

- ! l~ i

:.I:1: i : : ." :

, I l i 4F - f | " ' ~ i

! I t 4 - I 1 i-~ ' I - 1

:: I I-:.: -, t 14-

: i i : - D t , I •

- r I !'-* J t * *

i i i~- :i l ,r-t:

i i i i - I l t ,"i-

, ('-I +_L :t-l.E: -i-ii... - l - t 1"T" -r). TT -,l--4.. ,l--¢--

-i-i-~ - n i a

iLUl

20

Ze

16

12

8

I I I I I I i i I I I 1 I I I I

0

I ' , I I I

-Y!-t-i-. " ,

~ :-~.-7 , - 4 - - . 4 - - < - - ~ - / ~ - -

T , q ~ 0 0.2 0. q 0.6 0.8 1.0

30 F - 4 + I +

20 !,,,

- 'II- ' |RI¢ mm mmailiillml

mmmmmmmmm mmmmmmmmmme mlmmmmmmmml mmmmmmmmmm~ mmmmmmmmmml ~Jmmmmmmm~ mmmmmmmmml ~mmmmllBmml

~mmmmmmm~ amimmNmmi ,,mmmmmmmimml ummmmumml ammmmmmmmmmmml ~mmmmmmmi mmmmmmmmlml mmmmmmam~ immmmmmmmmmm immmmmmmmmt immmmmmmmmml immmmlmmmmml

0 0.2 0.q 0 .6 0 .8 1.0

t t

a. Time Figure 33. Wind tunnel captive t ra jectory and f l ight test

separation trajectories of the MVB wi th uncanted fins, M® = 0.50.

115

A E DC-TR-78-4

SYM ~ • TRB5 ~z ~a b) ~ TER CONF RIR. Zo (9 0.q8 t~ NONE 0 0 0 0 1 15 F-q O.OI 0 0.50 q NONE 0 0 0 0 [ 15 F-q OOI A 0.52 q NONE 0 0 0 0 l 15 F-q O.OI • 0 .50 4 NONE O O O O I 15 FLIGHT TEST

q 7 i r-t

: t i - - - Z: , rr- ~

. - -

16 - " II '+-:']

60

50

qo

3O

2O

10

0~

-10

-20

-30

-140

-50

-60 0

-; IF I 7 - l . l . '7 -

-_,L ~ -t- • • , . ;

- . . . ~ . . . . •

--4- d --'1, --4

B

- T " - + - , - . . ! -

-.- -i-- 1 - i - t - - o - ,

-i El- . . . .

H . . . .

~"_..2

-F ~- • - f . p _ °

'-" Ft r

P-~- I--4 P . -

• . l-r

q 8 12 Zp

~ 0 I I " I I I [ 1 1 ] .." ] i ] 1 1 I I ] l l l f l I I _ ' l l l i l l L I ~ I I I : I I I ' I ! I ': I I

2 0 / I i ! I i " I I I ; I I I • I ! I I l i I I ; i I I ; I I I : 1 1 I l l i l l ~ ! l l ~ l l l ~ l ] i _ L I T I l l l l l l I I I : 1 1

l O I / I ! l l I ! l l I I I I i l l L I I I I I i l l B I I I I I ! I I

,A~ 1 1 I I ! I i I I I I I I I I l I

o H-H-FH-t-]~-H'-t-H+I H-H+H-FT-F~-H-H-I

-1o FFH-Fi-H-t÷H-FH-H,,.,,. - r T T ~ - - -

-2o I - H - H H - H ~ i d - F H + I -3o I-FH+H--t tT,-Ff--FF~

-8 -q 0 q 8 lp

b. Displacement Figure 33. Continued.

116

A E D C -T R -78-4

SVM M. = TABS ~m ~ ~ ~ TEA CONF AIR. to • 0 ,50 3;' NONE 0 0 O' 0 I IS F-q 0.03 I~ 0 ,50 4' NONE 0 0 0 0 I 15 F-q 0.01 • 0 . 5 0 4- ' NONE 0 0 0 0 l |5 FLIGHT TEST

" t t t ! i !-tiBl-f!i '° :,61~*!t-~l-HtitL !t!lll:tl ..i°°

'tp f "

O(

-10

-20

-30

-qo

-50

-60

Iqlml mlmmm nmnem Ilnlllll ~ lllgll n m ml J mNII , l h l l l t l | | l , I

IiiI!I!Uli illigiltti I l l iM i illtillliii il. lliiit

TFFF - o - - -

--e-~ . . ~--e-e-+

!!)) _LLLi - e-.~p l-~-

" t - - 4 - - I - - + -

-I'TI"'r" -I-I"I-I"

_~,~ ~t)~ _~i-i_ -i-i-W-

. l ; : : : ; : ,

- , ' - l - l - r - i i i i

Zp

20

16

12

I l l l l l

! ) ! : : :

! 1 1 1 : :

: : : : : :

0 rrl '~-t~' 0 0.2 0.4 0.6 0.8 1.0

3O

2O

t0 At

0

L l l l l l l l l l l l l I l l l i l l l l l l l l I l l l l i l l l l l l l L I l i l l l l l l l l l l i i l i l l l l l l l l lmmmmmmmmmmml rmmmmmmmmmmm( ~mmmmmmmmmmm( ~mr~: mmmmmmm) ~admmmmmmmmJ nl~mmmqmmm~

;mu~mmm~)q

-10 --'~-~ TF-~- - - 4 : : : ; ; ~--4-.

. . . . - L L ~ -20 -~ . : . . . . : i i L~

- 3 0 -1-I i i i i i i , , , ,

0 0.2 0,q 0 .6 0.8 1.0

c. Time Figure 33. Continued.

117

A EDC-TR-78-4

e 0.50 3 [] 0.50 q • 0 .50 4

TRB5 6 n ~ 63 % TER CONF ~IR. ~o NONE 0 0 0 0 I IG F-q 0.03 NONE 0 0 0 0 I 15 F-q GOt NONE 0 0 0 0 I 15 FLIGHT TEST

0

-ii Xp

-8

-12

-16

60

50

I t0

30

20

lO zig

OI

- 1 0

-20

-30

-IlO

-50

- 5 0 0

:!

R

~t ; l I I f I

; - ' ' I t i l l . l I ~" !-"li !: |

.... V.I ,-o q • t

:I ii.i , . t . q - t - °

!it '-~' _ . "

ili . . . . . . . o , o-

:-! .i.i-i. ---i: :::--

i : : :

.... t -l--.q. 4 - - •

-g ~ 4

, - t ~ - t -

• ~

,-!-!-! j . . . . t - + - i - -

!2 . . . . . . .

l--lm l--i=

i - ~ i t - - t - - , -

I-" H-i-t- 8 I

Zp

ii; i ; - r

I ~-'

"1" I '

-~-

i i i " ° ~ .

-T'I

-4-. I

i - ~ 4 - , - - ° - . .

2 16

30

20

! 0 At

0

-10

-2O

-30 -8

I I 1 I I 1 ! I ! 1 1 I 1 1 ] | 1 I I I I I I ! I I I "., I I I i i I I I I I I l ! I I 1 1 I I i l l i I 1 1 1 I i l 1 1 1 1 I I i l i l I 1 I 1 1 I I ! 1 1 i l I I I i l I I I I I i l i 1 1 1 1 1 1 1 ! 1 I _ L J J _ L L L ~ J X i I I ~, i I

1 1 I F F F F I T - I I i I I i I

-LI O q B

Ie

d. Dispalcement Figure 33. Concluded.

118

MaD a TABS" ~1 ~2 83 8 4 TER CONF O.70 I NONE O O O O I 15

- - - -7"

Xp,ft

f ~ ---,'- ".. . . . _ ...- ..< J -" _..,.

J

. . , , . .

/

I0

,,,,,.,,. " " f

I0

t~ptt

a.

| lhf t I

Captive trajectory b. Flight test

Figure 34. IIl~'~mtion of wind tunnel captive traje~ow and flight separation trajectories of the MVB with uncented fins,

M = 0.50.

3~ m

K~ ~D O0 J~

A E DC-TR -78-4

Figure 35. Release sequence of the MVB with uncanted fins, no tabs, M = 0.50.

120

A E D C - T R - 7 8 - 4

SYM H. = TABS 61 I~ a ~3 % TEA CONF RIR. i~o B 0.70 I NONE 0 0 0 0 ! 15 F-q 0.03 A 0.72 2 NONE 0 0 0 0 ! 15 F-q 0.0! • O.70 I NONE O O O O I 15 FLIGHT TEST

tl

OI

-q X p

-8

-12

-16

W:ili t i i~! !t : ' i 1 i .-N,.~! l!i. ~,

ii i i - ~i! ill , i II

N-!._. ~r_-t~t:~-~t~tt -~- -,:~+ - i t

60

SO

qo

30

20

OI

1 0

-10

-20

-30

-qo

-50

-60

r t.: t f:!, I- l , t- I: t"

: i I

| - ! : " - I-, i,_ I-, "I- f" j--~, • 1-1 • I"I

: ! .._ .._, - i . i

-F l-;

• -F- - ~

- t - W

| , t ' ,

: ! ' r

.i! -1 4

t' , - + 1 , - i - i

"!!

- - 4 " ,

"!1 i

- i

-tl --..t-~ - . - t ~

"T! --4--1

Ze

20 ~ I I , , I l l ] l l J . d l l l l

16 1! I ! 1 / ±J _ - j ~

:r15 • i

_--.!

;,r ̧

0 0.2 O.q 0.6 0.8 1.0

k

a. T |me Figure 36. Wind tunnel e a p t i ~ trajectory and flight test

separation trajectoria$ of the MVB with uncanted fins, M, = 0.70.

~ u

1o i - T' - - r -

~ , . , _ L , . ~

0. ~, ~ -~- - r " .-.4--, ~

- I0 ~: -'-

1~~.!i3 ~~ -30 I ' "r , ,

0 0 . 2 0 . q 0.6 0.8 1.0

121

AEDC-TR-78-4

8Tx N. " TABS Ik I t I Ik ! Ik i TEA CONF AIR. i o El 0 .70 1 NONE 0 0 0 0 1 15 F-q 0 .03 A 0. ' /2 2 NONE 0 0 0 0 1 i5 F-q 0.01 • o .7o I NONE O O O O I 15 FLiGHT TEST

"q ' I x, 1i-!I i~I ~! !!. i

-"li:i-i ii!.~- !i '~IiI-I li.i ii il -16 . . . .

I : I •

so i[( i ~ . , : t . ' ; ; ,.:.r) :-!:i ;1 i,

qO " ' !I" I[14ii !'ii, ;!i i - ; ; i l ; i . . . . .

30 : , . T ' ; , . ,

r-i-, ii:i. ri.! i-il 20 i'f, ,,

1-::I '-I , , , i,,_,, 10 ) ' : t i ' f - i - t - i )+o-

i- i ; i i l i ; i-i i ~-i-

,-i4

!I.: ii!-.!h _,to ! t i i!7; i ,

-~° '~: " !I} i" _.o r tl i i.t i- " i i ! ° "

0 q 8 12 16 Zp

3 O l _ b l i l ] , ~ , , , , , , : : , I ] I I I ~.~ H-~b~-t+!-, ~ o , _ = . _ , . , , , , ,

' ° I } ~!:ti~t~!iii'-~*-~ t :. ,= -30

-8 -q 0 q 8 Tp

b. D i s p l a c e m e n t F igure 36. Concluded.

122

t~J

M== G TABS 81 ~ 2 ~3 ~ 4 TER CONF

0 . 7 0 2 0 NONE 0 0 0 0 J 15

- 5

,"" "~- / - ~ ~ - ~ - ~

., / / / /

/ /

/ / / /

/ 7 /

I0

I Xp,ft - 5

.~{ tc

e p f t

a. Captive trajectory b. Flight test

Figure 37. Illustration of wind tunnel captive trajectory and flight test separation trajectories of the MVB with uncanted fins, M = 0.70.

J X p .ft

I l l

o

~0

A E D C - T R - 7 8 - 4

SYM I~, - TRBS t t ~a ~ ~4 TER CONF RIR. i~o Aelq O 0.6e 1 NONE-|2 0 0 - 1 2 1 17 F-q 0.03 O O 0.70 1 NONE -12 0 0 -12 ! 17 F-q 0.03 O A 0.72 1 NONE-12 0 0 "12 t f7 F'q 0.03 O • 0.70 I NONE-12 O O - 1 2 I 17 FLIGHT TEST

1f! TIT

I I

tt+ !i!ilti: ~, i i ! l i ! - i i :!,I ~

~, ,ii!i+ ~

Tp I ' I I I I I I I I I I I I I I I I ] I I L I l l

' ' J ~ H - H - I 0 .. . 4 _ " ~ ' - - - ' + " ' ' " , ' . ~ .

:~ IN i:i-t rt I-i ftl~H:tl Ifi l l: i-~lli-i t1-~ ~-t-'+i

. n I l ' l : t i i ! l i ! - i l-l 't ' t t i " " l ' ;--I l-i .z.i i ,o I +! tt ~ t~ I h-i,~h-+.l, ! ,o I t-i! t i-141 ~! t i H H 7; I f-! ! l-!:f~t4:t l~+-i t !+

" ' o 1 ~ I !~-ti-+;i:t:+-+,~ ~i:t-illt+-tH~i~i ii

-'° I fi-+.i i !# i i "-ii H:i:l-~ -: i: Hi iii H 7li+H++ -,o I-~4;~H~+-t:H+H:~

-+o I t:t t It:H t t++it! IH.! t:f.

20 I I I I I I I | l l l I l l l l l I I I

11 1~ l i I I I I I I i I I I I I I I I I I I

', o H.--H+tl-t++t-b++ . tt+I-+C!~':+t-~:

0 0 .2 0 .q 0 .6 0 .8 ] . 0

A t i i i i l i t ] _ L i _ [ ' ~

.,o ~ ~ t ~ +H-H-H I-HnH-t-H~HH . _ H _ ~ L L L L i i i i i i i L L . L L L J

I l l I I i I i 1 t I 1 ! ~

-20 ,.-H-FH+I-H-H-FH-H-H_:EI . J - L L . L L L l i l i i i i I i i i I L l

- - 3 0 i i i i l [ / l l l i l l l l l l l r l

0 0 .2 0 .q 0 . 6 0 .8 1 .0

t 4L

a. T i m e Figure 38. Wind t u n n e l capt ive t ra jec to ry and f l i gh t test

separat ion t ra jector ies o f the M V B w i t h canted f ins, M = 0 .70.

124

A E D C - T R - 7 8 - 4

8YM I% a TRBS 5n 5~ ts % TER CONF RIR, ;Eo A# R (2) 0°68 I NONE-12 0 0 - 1 2 l 17 F-q 0 .03 O m 0 ,70 1 NONE- ]2 0 0 - 1 2 | 17 F-q 0 .03 O A 0 ,72 ] NONE-12 0 0 - 1 2 ! I'/' F-q 0 .03 O • 0 . 7 0 I NONE-12 O O - 1 2 I 17 FLIGHT TEST

xp ! a

-.t !2-, I - t

- 4 - : |-

- 1 2 1

-, , t ) , - 1 6 '

60 -~-

I . , . q f

5o 4."q .i

- : i -2

, .~ !

3 o -~ . - - l -

2o -~ ~ -F q . . . .

lO 1 - - o -

OI -'~ :

n - 6 - q - - I

I ~ r i

-30 . _, [_~

- 5 0

-60 0 q 8

I t li Ii I.!

.:L t ; ' I " I

" ' ; t : - o • I

• f • ! ,

, f • I , D - | ,

, ' 1 '

, - I , ~ J

o - , • • i

1"'! " ~ q i i - ] i

- - 4 - - " - I 0 , i

,p • ,

I I

- I ; ~ " ' "l-T " * ' - I T . . . . . . ,

I I - t • 4 , 4 ,

; ; i " • • - t - t

-r, :-!;: 4 O

" 4 " 4 . . . . 0 - - * ,

- t l . . . .

12 16 Zp

30

20

At I0

0

n m m u m m m m m n m m m m m u n n n n n n n n n n n u n n m n Lmnnunmnnmnnmumn

mmmmmmnmmmmmmn nnmummmm nnummmmn nnnmmmumummnmmmn

mmmmmnmnummn•ummn mnmmmmnmmmmmmmn

l l | | l l | l l | | l l - ' - ' | nmmmmmmmlmmnmnmn umnmmmmpqmmnmmmn nmmnmmm~~-unnmnmmmn nmluamnlb :~ummmm Imnmummnmmmmmmmmm a g m m l u n m m l m m u n

• mm • • n N,N|N, ,N | | , INR, , m , m , , , , , , , , i l l i l l m l l l m l l l n n

• • • I n I I , l l , | | l , l l l | | , n l l i l l l l l l l l l l l l l

- 1 0

- 2 0

- 3 0 - 8 -q

b. D isplacement Figure 38 . Concluded.

0 q 8 Tp

125

h.) o~

M . a TABS ~1 82 ~3 ~4 TER CONF 0 .70 2 NONE -12 0 0 -12 I 17

4 / * ~ ' ' ~ " ~ - - - _ . ~ . " ~

I 0

a. Captive trajectory

Xp,ft

" - r ~ ' - - - - - - - - - ~ ~ - - - / - -1

- - - - . . . _ _

l Xp. ft

r _ . ~ / f ~ " ~ - - - - - . . . . ~

~ r ~ ( ~

" ~ " , . , . . ~ , . , . , . ~ /

" - - - I

I 0 --

b. Flight test

Figure 39. Illustration of wind tunnel captive 1Tajectory and flight test separation trajectories of the MVB with canted fins, M = 0.70.

m cJ o

O0

A E DC-TR-78-4

~i ~i~; ~ ~: :L :i ii~ ~i~ i ~i~!i:!iii~!iiill I̧III•!~IIIII ~ ~i ~: !ii~ ~I ~i~ii~ ? ....

I

, i ~

~I~I~ZIIII'I!~•II~II~ i : :~ii ̧̧

~ ii ~ ,~

~ U , ~ i ~ i ~i'i~i~'~ ,,~' ~i:'i ~:~:~I~:~ ~ ~ :~ : : • ~:: i ¸

a. Uncanted fins, no tabs

Figure 40.

b. Two fins canted, no tabs

Release sequence of the MVB at M = 0.70.

127

A EDC-TR-78 -4

SYM H, " TABS ct ~a ~ N TEA CONF AIR. to A # e

(9 0 . 9 0 0 NONE 0 0 0 0 I 15 F-q 0 .35 0 13 0 . 9 0 0 NONE 0 0 0 0 I 15 F-q 0 . 0 3 - 4 0 • 0 . 9 0 0 NONE 0 0 0 0 I 15 FLIGHT TEST

:l ' . ~; t; . . . . : O:.,,~.,l~.!.i., ,~ " ' : : : ' : '"

_~ i , : : ~ : : : i : ! : Xp

-8

-12

-16

" : ! ' ~ ! I T T T I ' ' ' I ! T '

| 1 i ~ l l l l l l l l f : ' ' ' ~ ' ' ~ ° " ' ~ "~ I ~ - ! t : . . . . ' . . . . . . . , .

_q "i-~" ";" "*-

qo

30

20

ae 10

O,

-10

-20

-30

-qO

-50

-60

60 ~;

h so :i

I :

I •

I |

"F • I

fo

~ °

. i

. t

r - t

H" 14.

! i i ' i -; ~ - ~ l ; ' • , i : - , . . . . .

; - . t , . L-t ; I-; ; . , f , [ , ~ t F ; , ~ - ; ; I , , ~1~ Pf" " . ; . * * t . * ; ,.. ' '" . . . ' ' " ~ " [ ! l ' ' ' -

, , . | . : | . . ;

. : . . . ; : • l i

' "" ' t-1 t *-* 'P' ";- ~..~ .T . . . . . ÷

i . i .

. i , - - : , - e T ' e t . ~ ,

, i i ; ; - i i l

• / " * .~ t ,* ~ T t - t - - * ~ - t f " ~ . . . . t - * , * - ~

i ," |" ~-t't t ,--*-~-,

. . . . , , rt-.-t- .l~.-,-,

Zp

20

16

12

8

I I I l l 1 I I I I t ! . . . . [ I I II

I I i ~ i i " , , - . 1 1 1

F+ --r----~-F$. ---

- - f - " , - !"

(] _ t - I - I - 1 -

0 0 . 2 O. kt 0 . 6 0 . 8

30

20

I0 A t

O(

-10

-20

-30 .0

.H-, H-tiff1 F:ff: . . . . . . .

-;--;- ~ ~-M-. • . , I - -b t , - . . t . - . 4 - -

t " H - * ' -

. . : : : : L

0 0 . 2 0.tt 0 . 6 0 . 8 1 . 0

t t

a. Time Figure 41. Wind tunnel captive trajectory and flight test

separation trajectories of the MVB with uncanted fins, M . = 0.90.

128

AEDC-TR-78 -4

S Y M I ~ = TABS I~ n ~ ~ I,~ TEA CONF AIR. Zo &OR e 0 . 9 0 0 NONE 0 0 0 0 1 15 F-q 0 .35 0 rn 0 . 9 0 0 NONE 0 0 0 0 ! 15 F-q 0 , 0 3 - 4 0 • 0 . 9 0 O NONE O 0 0 0 I 15 FLIGHT TEST

- 1 6

60

5O

gO

3O

20

10

O~

-10

-20

- 3 0

-tlO

_q : , . i ! ! i : i X p . . . .

i i l:~ I ,~ ; , . I : ' ; ' ' ~ !

t ' = ~ = ' f t

- 8 : ; t ' : - i i . i - : ' : ; i . F F " | t t l ~ ~ f ; n , , ,

• r , " !1 ; : " . • " ; i i ' ; ; ; i ; - - 1 2 " * + 1 ' ~ ' ' - : J ' r "

• t ~ - !-t'-~ T ~ - : ~ ; ; : !~? ; t t - ~ : ~ ' ! "

-" ; - i-J : '

.; ; . t4. - i i ; '

"! ]-- 1 . . . . . . . 1-4- I . . . . . ~. I - . ~ q . ~ . : ~ ,

- 4 - ~ - 1 - ° . . . . ~ . I • n I

I T . . . . . . . , 4 ~ t * , !

4 - - -

4 - - , - - I

I , :

4 - o ; - 4 . I a I I

" I " * - - " - + - - - I I -~ -, " - f - - - - - - t - - 1 - - a ' '

-14- - - , - -| -t- - - + - -t-~ - ~ . . . . + - "t--~-- n

.-. : ; ; : :

• " t 4 - - i - J - 4---~

=,r- 4-4- -~--,- - _ : ! [ , '

RF ~-!"2 . . . . . -~ I1~ - ~ - - - I - - , - t - 4 -

iJ 44- i • l - t - - ~ - 4

.:.2 J_L- -i-Z- " " . . . . :!:!: i-~, " ' -50 , , ::

- 6 0 t i i J iiit

o, . 4

J , . - 6

• , t -

• - - ~ 4

• - o • s

o - o 1 "

' n o o .

n

4 - t - °

i - ~ - . -

• i ;

:-U. , I ,

w.~-1- : I i : - i

- 4 - - . - $ i i

• ~ " " ' 1 -

4--;4 ; i

- t - . . . . I - . , t -

. e . , ~ 4

- - 4 - 4 - - 4

"-L~ - 6 - - 4 - - , - - 4 - - o - - , - ~

i I

- - I - - ' + - - ' = - -

• O

. . q

. 4 - 4 - 4 - ~ - - e - -

i i ' -~~

tt 8 12 16 Zr

30

20

10 A t

0

- [ 0

-20

-30 -8 -q 0

b. Displacement Figure 41. Concluded.

q Tp

129

C~

M~ ~ TABS 8 I 0 .90 0 NONE 0

L . . - .,,*

~, __ --._= - 7 f .

j£ .i . -

b

I0

I Xp,ff

82 83 84 TER CONF 0 0 0 I IS

- 5 ~T'--

, . ~ t - , / , r

( I., , ' !

/ I I

,~'l ¢ /

I0

X p , ~

m

c) o

CO

ep,ft a.

%3t I Captive trajectory b. Flight test

Figure 42. Illustration of wind tunnel captive trajectory and flight test separation trajectories of the MVB with uncanted fins, M = 0.90.

AEDC-TR-78-4

SYM I~ = TRB5 I~ t I~ a I~ ! t i TER CONF RIR, Eo ~ N

e 0.88 0 NONE-12 0 0 - | 2 ! 17 F-q 035 0 [ ] 0 .90 0 NONE-12 0 0 - 1 2 ! 17 F-q 0.03 0 • 0 9 0 0 NONE -12 0 0 -12 I 17 FLIGHT TEST I ~ 0 . 9 0 0 NONE -12 0 0 -12 I 17 FLIGHT TEST

01

Xe "q -8

-12

-16

.Iftlt

l-l,rtt tl:!H-lliil! il;: iti;iil

I I I I I N IIIIIM IIIII I ! I I IU l

60

50

qO

30

20

] 0

0 I

-10

-20

-30

-qo

-50

-60

iitflilii!Uiii I l iMiiUli i ifliliiilffiili lflMMM iMBi i i i i i liiili AliiUil ilit, tliiii ii , iElilililili:: ililliiiliii ~ l l U i l l i l l l i l l l i l

I | l i l l l l l l l l l l l I l l l l l l t l l l l l I I I I , I ~ I I H I H l l l l

i l l l l l l l f l l l l l I I I M I I I I I H I I I I I M I I I l l l I I I l I l l I I ~ i ! 1 1 1 1 1 1 1 1 I I

20

16

12 Ze

8

0

! ! [ ! ! i l l .., " ' ' i i i i I I I I ; : ; : i I I I

-.4--4-4--~- - f -4--4.-+-

1 i 1 [ ; : : ; i : : ~ : : :

,-4-4-~ i ii~ ~ iiii

- - 4 - 1 - 1 - 4 -

N-4 4-4- ---,-o-~-~ I I : : : : : :

'-+'*'~-~" ~rd-l-t"

~--FF F-T~:FF 0.2 O.kl 0.6 0.8 1.0

I : I I 301,i~, I 1 [ 1 1

20,,:,, I l i l l

i;H4 AtI0,,,,I

I-M.-I-~

lU lL , i__i_iu

-10 ~ r ~ H+FF

-20,!,i i

-30 ~-T~, 0 0.

: ! ! 1 ! ! !

: ; ; : : : ;

: k i ! i i i

~ i i i i V I I I

2 O.q 0.6 0.8 !.0 t. t

Figure 43. a. Time

Wind tunnel captive trajectory and flight test separation trajectories of the MVB with canted fins, M= = 0.90.

131

A E D C-T R -78 -4

SYM H,. • TABS t, t a b 9 ll~ TEA CONF AIR. Zo AOR

0 0.88 0 NONE-12 0 0 - | 2 ! 17 F-¼ 0.35 0 El 0.90 0 NONE-12 0 0 - 1 2 l 17 F-~ 0.03 0 • 0.90 0 NONE -12 0 0 -12 I 17 FLIGHT TEST I f 0 .90 0 NONE-12 0 0 - 1 2 I 17 FLIGHT TEST

o - ~ :-:-i- ---i- : . ~ k t t , l t l x,- ' t t - ~" I! -i !

- ft-~:-i-t-t-i i t ! t-i-t-tti I !ii I

60

50

~0

30

20

10 Ae

OI

-10

-20

-30

-~0

-50

-60 0 LI 8 12 16

Zp

30

20

!0 At

I I I I I 1,,11',III I 1 1 1 1 1 1 1 1 I 1 " 1 1 . . . . : : : .- I l i l l I 1 1 : 1 ! ! ' ! _ 1 1 i l

1 i : : : : : : : -

I+H-J-I 1 j i

~ i l lL -tO __Mill_

--ii iii -20 - ! ! !d

-30 - r t l ~ - -8 -q 0


tl ¥p

8

132

M• a TABS BI ~2 85 8 4 TER CONF 0 .90 0 NONE -12 0 0 -t2 I 17

,J

I

/ / / / / . _.~.t / /

/ /

Xp.ft

•pit

io -

a. Captive trajectory

~- , ~ ~ ~

( ( ~ . / / / / / /

/

/

illmft

I0

I Xp, ft

/ / /

/ / / /

/ / / / ( /

( . J

b. Flight test

Figure 44. Illustration of wind tunnel captive trajectory and flight test separation trajectories of the MVB with canted fins, M -- 0.90.

rn o (~

"]1

CO

A E D C - T R - 7 8 - 4

S~[ If,, ~= TABS 61 ~ 6l N TEA CONF AIR. Zo AeR O 0.g0 0 TES -12 0 0 - 1 2 1 tB F-q O.t6 O 13 0.90 O TES -12 0 0 - 1 2 1 18 F-q O.iS - iO '= 0.90 0 TE5 -12 0 0 - 1 2 ! 18 F-q O . 1 6 - 2 0 v 0.90 0 TES -12 0 0 - 1 2 1 18 F-q O . t 6 - 4 0 • O.90 O Y E S - 1 2 O O - 1 2 I 18 FLIGHT TEST

. . . . . . ; ; ; . l - ~ - i l l l -

~ + l , t l + , 4

. . . . . . . . . l i t 1 0" - ~ . . . . 4 " + I- l

• I + ' I '

Xp . . . . . . . . . . . . . . . . ,+,1 '

-8 _Li.i.iii: iJi -i ............ ii-:

- 1 2 4 - i i i L i . i i.: :. . . . . . . . . + ' + + ' t '

- 1 6 - r , v T t r _~rr -+-

Tp ~ H - H - H + H + H - H + H + H 4 o ~-FZ-EL-~.-~-! +FH-H-H

~ J ~ i r t - + ~ / ' º l l [ l l l l l l l l I ; l l l º l l l i l l l l l l l l l ] l

S 0 . . . . . . . . . . . . . .

- + 4 - i ~ • • ~= 4--~ 4 - ~ -$ -q~ -4 -

50 T .M?! ' !- !-r!T,.'-.t-!'"

qo T t ! ~ ? t !--! r!.+q-. ! t - . I -+ - - i - - l - ~ + 4 - - i - 4- ! -~ "-~-0--#- I - , --+4-I +-tl I , ~ - - I + + + k I -

30 -1-1-1-rM r ?-tl-!-rt-l-

2 0 - * " . . . . . . !'I T M I" ~-I: . . . . . 11-rt ' l ' . + / - - i - • - + - + 4 ÷ + •

+ I + + + + m I

+ . i - . - ~ + ~ .-l--.Ik- 4 ,4- ~ i .- i~ ,

~ 1 0 ...;_ii . . i . t i_ . i . : . i 2;.Li_, . . . , , - + - ~ - ~ l - t l , l l . - - . + ~ - + - + - - + - o

l]: : : : ; : :: : , , --. : : ~ 1 -"

10 - t~ ~ . . . . . . . . .

A A

- ~ U : : ; : : : : : : : : : : : - : " - t t ~ - l t t - + l - - "("41--4 + 4-.4.-- -.-4--1. i • - t - ÷ 41-, "-'P'+--4 -4--1,--+-41,--

-30 Trl ~Tt-T~. .TTt T. -.~_~1.~-i- k - , - , . , . . . . """' ~ :LLLi- --4-+41 ~t- t ,w, t - .

. I . l O : : : : : : _ - ; : : : : : :

-50 T':'-! -E~- ~ .-M.! T . t-+-r . . . . . . . . . . _ . . . . 4..4-1 - . D ~ 4

-60 -,"-I"1"I-I-'1- : i i : i i i

Zp

0 1 1 [ 1 I l l l

i i i i i i i ' ' ' ' I I I I 16 t , i , ~ , , I I I . . . . . I I 1 1 : : : : : ; : ; ; ; ;

i i i i i i i i i l j

l l i i l | i i I - I - I - I - L - I - L .

8 ~.4-,I .- l- l i- .- i i

_ l - r1 "+

0

I [ 1 1 i l l

I I I I I I |

: 1 | | I I | l I n n |

i i i i f i l l

| | 1 ! ! ! !

i i i i - 1 - M - P

-I-I-I-- . . i

0.2 0.q 0 .6 0 .8 1.0

3o I', I I ~ I i ~ 11 ] ' ' "

20 i:: ~ i l l I"',, • i i ~ ! ! ! I ~ i i i i . . . I I I I I I

.,,to +~ iiJi Ill'"',,,, : | 1

- 1 0 . . . . . . . . . . . .

~ - - ~ d - 1- - ~ ' -.4-M.. - 2 0 ; • : " : : : I I , , , t

~ H - - T . ~ . ~ ~ . ] ~ - ' - ~ ' - ' - , . . - , p . . p - + - . ~

P,,,,ll-- ~ - - I -4 - -4 - -1 - - i - - t - . P - • - .

-30 . . . . . . . . . . . . 0 0 .2 O.LI 0 .6 0 .8

t t

1.0

Figure 45. a. Time

Wind tunnel captive trajectory and fl ight test separation trajectories of the M V B with canted fins and tabs, M = 0.90.

1 3 4

AEDC-TR-78~

8YM

0i

Xp -q

-8

-12

-16

60

50

qo

3O

2O

10 Ao

O=

-10

-20

-30

-qo

-50

-60 0

!% = TRB5 5 t e, z ~0 % ?ER CONF' Rift. 2 o L~BR 0.90 0 YES -12 0 -12 I I 18 F-q O.m6 0 0.90 0 YES -12 0 0-12 1O F-4 0 .16- IO 0.90 0 YES-12 0 -12 I 16 F-q 0 . , 6 - 2 0 0.90 0 YES-12 0 00- I : 18 F-q 0 . , 6 - 4 0 O.90 O Y E S - 1 2 O - I I . FLIGHT TEST

IiPflilllllll lllmiilllllill fliP.tglllgl HI!MMI

8 12 16 Zp

30

20

lO At

0

l l l l l l l l l l | l l | l l n l l l l l l l l l l l l l l l l l l m l l l l l l l l l l n l l U m l i l l m l n l l l l U l l l l l l l l l l l l l l l l l l l f l l l l l l l l l l l l l N l l l l l l n l l l l l l l l l l l f l l l l l m n m m i m m n l l n l l E ~ l m m n m m l n m B n | n i l I R m m n m m m m l m l l m m i l i l f l i l i i l B I I l l l U m l m r , l n l l i l l l i m m l n l l i J m l n l m m l I I i i B m l l I l l l l l l l immmmmmrmmmmmmmm mmmmmmmmmmmmmmmm mmmmmmmmlmmmmmmmm mnmmmmr,lmmmmmmm mmmmmmhmmmmmmmm

lmmmmmmmmmmmmmmm mmmmmmmmmmmmmmmm ammmmmmmmmmmmmm ammmmmmmmmmmmmm

-I0

-20

-30 -8 -4 q

Yp


135

o~

• Mw a TABS 81 ~2 ~3 84 TER CONF 0 .90 0 Y E S - i ? . 0 0 - t2 I i l l

C

f

,,_~r," ~ ~ ~ .---- . . ~ f

f" I I I

C~,~..~/I I-

I0 -

I Xp,f l ~ ~ ~ . . . . . i _ ~ \ "§ Xp,ft

.o, 1 1 I / - / / / ,.., _.. / z I / / / / / / / /

v..,.J~,,! I / i I

I I / ! ~...I ~J

I0 -

a. Captive trajectory b. Flight test

Figure 46.

tl,.tt

Illustration of wind tunnel captive trajectory and flight lest separation trajectories of the MVB with canted fins and tabs, M . = 0.90.

i pw ~.J # #

I , /

! / / /

! / /

! /

U

~> m Cl c) -n

co i~

A EDC-TR-78 -4

~ : ~ i ¸

/ /

a. Uncanted fins, no tabs b. Two fins canted, no tabs c. Two fins canted, with tabs

Figure 47. Release sequence of the MVB at M= = 0,90.

137

A E DC-TR-78-4

Xp

l'p

SY.',! H= " TRBS I h i~ e 1.02 0 NONE 0 0 13 1.02 I NONE 0 0 A 1.02 0 NONE 0 0 • I 02 0 NONE 0 0

i s ~ tEfl CONF RIR, i~ o &OR 0 0 l 15 F-q 0.03 -40 0 0 l 15 F-q 0.03 -40 0 0 1 15 F-q 0.:55 0 0 0 I I§ FLIGHT TEST

q

O:

-q

-8

-12

-16

: i i !,! .t~_t!l ' tl l i : ;~i i l :

" ! l i t ' ' , ! ! , ' ; !

- - :4~ i . : "~ .

,:-I ! " " ' l : ' ! ' t " l . l ; i i i . t ; | - i . t l t ~ ! : : t !

| I I I | I I I I 1 l I I l l I , , u _ , , , : , , , ,

n . Z . [ . ~ . z . , ; . i ! , ~ ! ! ~ l i i l "

I I I i / 1 / I 1 1 t t ~ ' + - ~ - ~ __q I T N - r . T , ~ I T t T 11-°-tl

60

50

qo

30

20

z~e 10

01

-10

-20

-30

-q0

-50

-60

Ii-i

"i i ! -:... i.

r:r, -

.

!:! I

d ,

, Q.,

"I-'

it i' ; l ,!

~i L:- ' 1 " t'T,"

~ j . . i :

-'- I ' .

; .g~L, g [ ;4- ;...-, !-f.,

~'I"

20

16

12 Zp

8

q

0

I I I I I ] I

I I 1 1 1 1 1 1 l l l l l l l l I 1 " 1 1 1 1 1

H:. ÷t ._~+.. fffH,~!

.l_u~_u-

0.2 0. q 0 .6 0 .8

30 i -H+I i i i i

~ I , - t+1 , t l i '

At t O ~ " ' r ~ ' - ~

=T--t-t- I I 1 1

| ' 1 1 ~ 1 I 1 | !

_ l O , ' l l i!]!"

20 :T ! -~

1 .0 0 0 . 2 0 . q I 0 . 6 0 . 8

t. t.

.0

Figure 48. a. T ime

Wind tunnel captive t ra jectory and f l igh t test separation trajectories of the MVB w i th uncanted fins, No. 1 TER stat ion, M® = 1.02.

138

A E D C - T R - 7 8 - 4

8YM It= = TRB5 6= 6 a b= ~ TER CONF RIR. Eo A9 R (9 1.02 0 NONE 0 0 0 0 ] 15 F-q 0 0 3 -40 m 1,02 1 NONE 0 0 0 0 ! 15 F-q 0.03 -40 "~ !.02 0 NONE 0 0 0 0 I 15 F-LI 0 35 0 • 1.02 0 NONE 0 0 0 0 I 15 FLIGHT TEST

1 " "

x- I-i-I-I I i-T-! l-Ti ! " I t - - t - I t H I i - t ! I .

60

5O

LtO

3O

2O

10 Ae

0

-10

-20

-30

-qO

-50

-60 0

i " I --I--, !:i

~ . . $ .

L J,

-!

. l , - + .

VE

t_o., q 8 12

Zp 16

16

12 Ze

8

It

0

30

20

I0

0

i J- , : l : - l l . L . ; i . t , , - t • .# 4 - 4 - . -

" ] ' • ' I " ' t ' t t - - f • I '

...... ...! !+, L T i l l -.-t

- t , , . ~! !~ ; ~-: . . . . . . . i . . _

i

- i ' " ' - T " • I - t -1- i ' -~ ' . ~' • 1 t - l - - T-I-! I " l t

r : : . . . . . .

' r r l - . . . . 4, -,

-tO

-20

-30 -8 -q

] I ! ! ! , , ~ ! ! ! ! J . . i l l l i i i i i i i i ! I I 1 I I 11 I 1

' i i i r ! ! ' : : :

i i i ~ : , :--" , ,~ ~ i i ! ! : i

- - ~ . ~ . - - ~ 4__!!! : , ,_ 444

....... -: a-.l-l-..-,-I -- , , i l l II

Tp

b. D isp lacement Figure 48. Concluded.

139

¢ , _ _

~__>,,~ ..._- f

/

b

I0 -

f /

l

J

i . a TABS 31 3 2 3 3 3 4 TIrR CONF l . O 2 0 NONE O O O O I 15

I x p , f t

-_----~17_-> ~ -- .-" "/-A - _ _ ' r / " / ~,/_/) . ,"V' ," ,:/.: C..-~ -1 / / i / /

/ / / / / / / / / I"(~,.>./, / / / /

/ / t

Xp, f l

I0

3~ m

"11

Go 4,

eth" a . Captive trajectory b. Flight test

Figure 49. Illustration of wind tunnel captive trajectory and flight test separation trajectories of the MVB with uncanted fins, No. 1 TER station, M = 1.02.

A E D C - T R - 7 8 " 4

sYe I% = TABS % la Q 1.00 0 NONE 0 0 B 1.02 0 NONE 0 0 A 1.0q 0 NONE 0 0 • I. 0 2 O NONE O O

i~ N TEA CONF" AIR. leo ASR 0 0 2 ;6 F-q O.OI O 0 0 2 16 F-q O.Oi O 0 0 2 16 F-q O.OI O O O 2 16 FLIGHT TEST

' f l-ft-I-tt.! 0', _, -I.1t! x, ,t:t ili! ]t

- 0 '

.tiii-ltl-!-titt -16

~ p II 11 I 1 r I | u I ( I i U U l l l l U ~ I ] I I I I i I i "

t.]!l i fl • i t ~ . 1

l-iili .tl l:-!!fti !l [---!:!-I !i:tl

I f

IN

60

50

q0

30

20

ae t0

04

- I0

-20

-30

-q0

-50

-60

2O

16

12 Zp

8

q

0 0

+ - ~

4-4~ t-t-1

-+ - t - ~

0.2 0.q 0.6 0.8 1.0

30

20 ,.,o)) Ik -,o,[i ,j

- 2 0 f i

-301 i

immmmmmmmmmlm limmmmmnmmmml mmlmmm!mmmmm |mmmmmmmmmmmm Immmmmmlmmmmm mmmmmmnmmmmm )BmmmBmmmmm mummmemumm |mmmmmmmmmumm mmmmmmmmmmmm |mmmmmmmmmmmm mmmmmmmmmmmmm ,:qnmmmmmmmmm h~LlFmmmmmmmm m~m~~ • • • • mm m**,lm|mlm|m I m ~ l l ~ l m l l l l l m i i i / B k ~ - ~ m m l m m I l l k l l . ? ~ ] l B I I m m m l m u ~ l i m a m mmDllmOllilm mmm . • ) • mmm&,Iml~l|m i B l B m m B m m B m m i

+. +,

I i n ! i l i l l l l

I l m m l l I m l n n l I I I H I l i i l l l l IBNBNB I I I H I I l l l n l I m l m m m I m I B m l I l n l l l l i i l l l I I I n l m I m l l l l mmmmmm mmmmmm mmmmmm mimlmmi mmmmmm mmmmmm immmmm nmmmmm mmmmmm

0.8 1.0

a. Time Figure 50. Wind tunnel captive trajectory and fl ight test

separation trajectories of the MVB with uncanted fins, No. 2 TER station, M= = 1.02.

141

AE DC-TR-78-4

SYM I~, == TABS ~i ~z ~s I~ ?ER CONF AIR, i~o A 8 R

(9 l .O0 0 NONE 0 0 0 0 2 16 F-q 0.01 0 13 1 .02 0 NONE 0 0 0 0 2 16 F-q 0.01 0 & i .Oq 0 NONE 0 0 0 0 2 16 F-q 0.01 0 • 1 . 0 2 0 NONE 0 0 0 0 2 16 FLIGHT TEST

o,! -tl

Xp

-12

-ta 611

50

g0

3O

20

10

0

-10

-20

-30

-q0

-5C

-6C 0

- - ~ , : ; l i

i" t . , , . . . ~ . . N ~ "' I I I t 'I, " t + + B ~

+.+ i l i i . , : : : I ' " + ; . ]+-; t , , , . , ,

I " ' ! I ~I " t : •

i . + .

1

- t i + i ,"T- + I

E 1.1

+ : i r ' ' t '

: ! " : : " ~ " I '

' : i l l | . : :

11 ' , ' '

I;- [:.::

; - i - ; . , . ~ . .

"" !- "-t <' ? " + I

I i + . i + .+-+- :.,--. t - t - - -

+-I .i .. :- I r ' t l h t !+. F! -FH- ' - ' ~T! -H ,,.,

t i '

12 IS Zp

s ° l l + l l ! , , l , l , , , , , , , ' - I I i l i l l l

L U I 1 1 1 H I I I 1 i I ! I o n a i l 1 1 i i 111 I 1 1 11 1 1 L V L L 1 1 [ J I ! I 1 1 1 1 1 1 1 1

I t I ! - I - I ! ' I I 1 1 I ! [ 1 1

to t +: H+H:+t+H H - ~ I_.~ i 1 . l _ [ _ l . J . l I I : I i : f I

1 1 : 1 ! ; + I PJ:LU-L-H,, ,, ,,I i t - ! i I t,,,i,I 1 1 1 i i : I

0 l J . i i i_ . I . / _ T _ L l I I I I I I I . . l I_J .J I i / A l 1 I I 1 I ; I

F:~:t H l i i H + ~ I-I

A t

-I0

-20

-30 ~ -8 -~

+ F;

0 4 8 Tp


|42

A E DC-T R -78-4

~ ~ ~!~ ~ ~!iii! ¸̧ ~!i!~iiii ¸

i i i : i

i~ i l ¸ ;

i ¸ ¸

~ . . . . . . . . . . !~i~ 1 t iii '~

,,, . ~ -

a. TER station No. 1 b. TER station No. 2

Figure 51. Release sequence of the M V B with uncanted fins, no tabs, M = 1.02.

1 4 3

sYMeOL CONFIG ~ 81 ~?.. 8 3 8 4

0 I o o o o o I"I I O - 12 0 0 - 12

I 0 - 1 2 - 1 2 - 1 2 - 1 2

- - - - ~ Ref. 7

-8oo! -600

-qO0 Cmcl*r ~

-200

0

l i

Moo O. 5 0 I J

200 - " -50 -q0 -30 -20 - [ 0 0

! ]

M = 0.70 oo

I0 20 30 q0 50 -50 -q0 -30 -20 -10 0 mS

10 20 30 q0 50 o¢$

-800

-600

-qO0 rmcl*Cm

-200

0

1 !

Moo - I.I0

I I

I !

Moo = 0 . 9 0 1

I [ 20050 -q0 -30 -20 -10 0 l0 20 30 q0 50 -50 -q0 -30 -20 -10 0 10 20 30 q0 50

O[ S O[ s

a, No tabs Figure 52, Effects of angle of attack on the pitch<lamping

derivative of the MVB.

111 C)

"n

0o &

l i l

u i

-800 ~ i M = 0 . 5 0

Oo

-600 I ,

-qO0 C~.C~

-200

0 - ~ ~ ~ ~ 200

-50 -q0 -30 -20 -I0 0

-800

-600

-qO0

0

1 I

= 0 . 9 0

I 1

200 L I I I I -50 -q0 -30 -20 -10 0

SYmSOL CON~IG 4~ 81 SZ 83 S4 O 2 o o o o o [ ] 2 O - 1 2 O 0 - 1 2

2 - 0 - 1 2 - 1 2 - 1 2 - 1 2 _ m R e f . 7

I !

M = 0 . 7 0 O0

1

i" , I ,

I0 20 30 LIO 50 -50 -LIO -30 -20 -10 0 lO 20 30 qO 50 wm$

I I

M - I . I 0 ¢ o

l I

• I I

~~~ ~ ~ ~~-~"'~o j -~_._~~~.~,; r~ . , I I

10 EO 30 qO 50 -50 -qO -30 -20 - I0 0 as

b. With tabs Figure 52. Concluded.

lO 20 30 qO 50 ~s m

o

¢o L

Table 1. Full-Scale Store Parameters

)> m

o

-n

co

m

4~

P a r a n e t e r S b m t'~_mq/Cnr S e t No. - I y y / I z z Xcg

1 .396 1 .333 24 .86 6 5 . 0 / 6 5 . 0 1

2

3

4

5

6

7

8

9

10

11

12

13

14

26 .64

26 .57

26 .57

26 .45

26 .45

26.01

26 .636

26 .356

7 7 . 3 / 7 7 . 3

7 6 . 8 / 7 6 . 8

7 7 . 3 / 7 7 . 3

7 7 . 3 / 7 7 . 3

7 7 . 8 / 7 7 . 8

3 .042

3 .042

2 .708

2 .708

2 .708

3 . 0 4 2

3 . 1 3 0

3 .141

3 . 1 3 0

3 . 1 3 5

3 . 1 1 5

3 . 0 6 9

3 . 0 5 2

3 .083

- 2 4 . 0 / - 2 4 . 0

- I 0 0 / - I 0 0

- 2 4 . 0 / - 2 4 . 0

- 1 0 0 / - 1 0 0

- I 0 0 / - I 0 0

- 2 4 / - 2 4

-76 / -76 - 1 0 0 / - 1 0 0

- 1 2 5 / - 1 2 5

- 1 2 5 / - 1 2 5

-125 / - -125

- 1 0 0 / - 1 0 0

- 1 2 5 / - 1 2 5

- 1 2 5 / - 1 2 5

Fz I

1 ,200

1 ,500

1 ,200

,1

Fz 2 XL I XL 2 Z E

- 0 . 1 7 3 0 .255 m m m

m

m

1 ,500

- 0 . 5 0 5

0 .833

- 0 . 0 8 3

- 0 . 0 7 3

- 0 . 0 8 3

- 0 . 0 8 3

- 0 . I 0 0

- 0 . 1 4 5

- 0 . 1 6 2

- 0 . 1 3 2

m

M

m

- 0 . 8 3 3 3 0 .342

0 .255

C o a f i ~ No.

1

i

4A

4A

T a i l Conflg

6 - 6 , - 6 3 - 6 4 - 0 I N~ Tabs

61 -62 -63 -64 - - -3 No Tabs

6 -62-63-64- -6 1 No Tabs

6 1 - 6 2 - 6 3 - 6 4 - - 9 No Tabs

6 l - b 2 - 6 3 - 6 4 - 0 No Tabs

6 1 - 6 2 - 6 3 - 6 4 - 0 No Tabs

Table 2.

~r m M~ def~ . -

0.50 4

0.50 8

0.70 2 0.70 2

0.90 0

0.90 I

1.tO I

1 .10

0.50 4

0.50 8

0 .70 2

0.70 2

0.90 0

0.90 I 1 .10

I . 1 0

0 .50 4

0.50 8 0.70 2

0 .70 2 O. 90 0

0 . 9 0 ! 1 .10

x . l O |

0.50 4

0 . 5 0 8

0 . 7 0 2

0 . 7 0 2

0 .90 0

0 .90

1.10 1 1 .10

0.50 4

0.50

Identification of Captive Trajectory Test Configurations and Test Conditions for FJ, C Aircraft

He f t

5 ,000 I

20,000

5,000

20,000

5,000 20,000

5,000 20,000

5,000

20,000

5,000

20,000

5,000 20,000

5,000

20,000

5 ,000

20,000

5 ,000

20,000

5,000 20,000

5,000

20,000

5,000

20,000

5 ,000

20,000

5,000 20,000

5 ,000

~0,000

5,000

20,000

Pylon S t a t i o n

S t a 2, 3 :

TER Config

5 t a 1: M s t r x r Dummtrs

T r a j e c t o r y C o n d i t i o n

I n i t i a t e d f rom C a r r i a g e P o s i t i o n

I n i t i a t e d a t Lanya rd o f 1 . 5 f t

I n i t £ a t n d a t Lanya rd o f 1 . 5 f t

P a r a m e t e r Se t No.

(FZ1 - O)

1 (FZl - O)

Run I d e n t l f l - - r a t i o n No.

3

4

9

10

l l

12

15

14

1 9

2O

23

24

25

20

28

27

31

32

33

34

36

.37

39

38

43

44

47

48

49

50

56

57

140

143

m O O

nn

CO

ConflK Ms.

4A

4A

4A

5

5A

T a i l Conf lE

5 1 - 8 2 - 8 3 - 8 4 - 0 Ms Tabs

6 1 - 6 2 - 8 3 - 6 4 - 0 No Tabs

5 -8 - 6 3 - 5 4 - 0 1N~ Tabs

6 -8 -63-64--lg 1 ~o Tabs

8 1 - 6 2 - 8 3 - 5 4 - 0 No Tabs

~1-62m/;3-64--12 No Tabs

4 F i n s a t 0 Cant No Tabs



M W

0 . 7 0

0 . 7 0

0 , 9 0

0 . 5 0

• 0.50 0 . 7 0

0,70 0.90 0 . 9 0

1 . 1 0

1 . 1 0

0.50

0.50 0 . 7 0

0 . 9 0

0 . 9 0

1 . 1 0

1 . 1 0

0.90

deg

2

2

0

4

8

2

2

0

1 4

8

2

0

H, f t

5.000

30,000

30.000

5,000

20 ,000

5,000 30.000

5.000 30 ,000

5 .000

30 ,000

5 ,000

30,000 20 ,000

5,000 30.000

5,000 20 ,000

5,000

20.000

5,000

30,000

5.000

30.000

5,000

Table 2. Continued

P y l o n TER T r a j e c t o r y P a r s m o t e r Run I d e n t i f i - - S t a t i o n Conf t5 C o n d i t i o n S e t No. c a t i o n No.

m

n

m

8

4 p

5 t a 1: M e t r i c 5 t a 3, 3 : Dummies

5 t a 1: i ~ p t y 5 t a 3 : M e t r i c 5 t a 3 : D u ~ ¥

S i s 1: Empty 5 t a 2 : M e t r i c 5 t a 3 : Dummy

5 t a 1: Empty 5 t a 2 : Empty S t a 3 : M c t r l c

S i n 1: Empty 5 t a 2 : Empty 5 t a 3 : M e t r i c

S t a 1: Empty S i n 3 : M e t r i c S t a 3 : Dummy

5 t a 1 : Empty S t a 2 : M e t r i c S t a 3 : D u l l y

S t a 1 : Empty 5ta 2: Empty 5 t a 3 : M e t r i c

I n i t i a t e d a t Lanyard o f 1 . 5 f t

I n i t i a t e d a t Lanyard o f 1 .5 f t

I n i t i a t e d a t Lanyard o f 1 . 5 f t

I n i t i a t e d f ~ C a r r i a g e P o s l t l o n

I n i t i a t e d a t Lanyard

I ( F z I " 0)

I ( F z l - 0)

I (FZl " O)

I

o f 1 . 5 f t

q

I n i t i a t e d f rom Car r t aMe P o s l t i o c

( F z ; - O)

14S

146

149

91

62

55

96

57

68

73

59

141

| 44

147

151

153

157

159

78

79

51

90

84

85

87

m O c~

co

Table 2. Continued

' ,0

C o n f l g No.

9

I 0

I I

12

12

T a i l Conflg


6 1 - 6 4 - - 1 2 6i-~3-o

Tabs

61-64,---6

Tabs

61-64---9

- T a b s

6 . - 6 . - - 9

No T a b s

M ~) d ~r .eW H, ft

0.90 0 20,000

0.50 4 5,000

0.50 8 20,000

0 . 7 0 2 5,000

0 . 7 0 2 20 ,000

0 . 9 0 0 5 ,000

0.90 I 20pO00

1.10 ! 5,000 1 .10 | 20,000

0.50 4 5,000

0.50 8 20,000

0 . 7 0 2 5 ,000

0.70 2 20,000

0.90 0 5,000

0.90 t 20,000

1.10 1 5,000 1 . 1 0 20,000

0.50 4 5,000

0.50 8 20,000

0.70 2 5,000 0 . 7 0 2 2 0 , 0 0 0

0.90 0 5,000

0.90 [ 20,000

1.10 6,000

1.10 20,000

0.50 4 5,00

0.50 8 20,000

0 . 7 0 2 5,000 0.70 2 20 ,000

0.90 0 5,000

0.90 0 20,000 1.10 0 5,000

P y l o n S t a t i o n

TER C o n f t g

S t a 1: Empty 5 t s 2 : Empty S t s 3 : M e t r t c


5 t s 1: M e t r l c 5 t s 2 , 3 : Dummies

I n i t i a t e d f rom C a r r t a K s P o s i t i o n

PaTameteF S e t No.

Run I d e n t i f i - c a t i o n No.

86

206

209

211 210

213

214

22O

218

105

196 198

107

200 2O2

205 204

54

55

57

56 71

90

72

73

165

168

173 171

191

185 192

m

o

-n

oo i

C )

C O n f i g No .

13

14

14A

i

T a i l C o n f i g

6 1 - 6 . - - - 9 6i-61-o

No T a b s

I

q~

61-6 t -6,-o

Table 2. Continued

P y l o n 7ER Run I d e n t l f t - S t a t i o n C o n f l g c a t i o n No.

Sin 1: M e t : l o S ta 2, 3 : Dummies

S t a 1 : M e t r i c

I n i t i a t e d f z ~ m C a r r i q e P o s i t i o n

? r a J s c i o r y P a r u e t s r C o n d i t i o n S e t No.

1

5

1

2

5

1 g

3

4

4

5

2

1

2

3

4

1

2

3

4

5

1

2

3

1

2

1 g

1

1

1

2

,r 1

S t a 2 , 3 : 6 3 " 6 4 " ~

I

61-62 - I n i t i a t e d a t L a n y a r d o f 1 . 5 ~ t

l U

143

146

147

148

151

16o

153

161

127

128

132

131

134

135

138

141

119

12o

121

122

123

124

125

126

234

233

231

230

228

229

226

225

224

m C~ c~

co

m

Con t g Ni .

T a i l C o n f t g

6 . - 6 9 - 6 ~ - 6 . - 0

I

1 6. - 6 2 - 6 ~ - 6 . - 0

J" No T~bs "m

No 1~.bs

O. 0

1. 0

O. 8

O. 8

O. 0

O. 0

O. 0

O. 2

O. 2

O. PO

O. ,0

1. )2

~r deg

0

4 . 0

3 . 0

4 . 0

4 . 0

1 . 0

2 . 0

1 . 0

1 . 0

.1.0

- 1 . 0

- 1 . 0

- 1 . 0

0

0

1 . 0

20 , I00

5, ~00

20 , ~00

5, ~00

20 , pO0

20 , ~00

20, ~OO

8, )00

4, ~00

4, bOO

5, )00

5, )00

5, )00

Table 2. Continued

Py lon S t a t i o n

TkR C o n f i g

B t a 1: M e t r i c S t a 2 , 3z 6 3 - 6 4 - - 9

Tabs

Sta 1: M e t r i c 8 tn 2, 3:

61-62 -

Dumznlea


I n i t i a t e d a t L a n y a r d o f 1 . 5 f t

I n i t i a t e d f rom C a r r i a g e P o s i t i o n l e o a - 0 " )

I n i t i a t e d f r o m C a r r l a p P o s i t i o n 1 ~ 0 a - - 4 0 )

I n i t i a t e d f r o m C a r r i a g e P o s i t i o n ( ~ 0 a - --401

I n i t i a t e d f rom C a r r i a g e P o s i t i o n ( ~ e a - o )

I n i t i a t e d f rom C a r r i a g e P o s i t i o n ( ~ e a - o )

I n i t i a t e d f rom C a r r i a g e P o s i t i o n ( ~ e a - - 4 0 )

I n i t i a t e d f rom C a r r i a g e P o s l t l o n (~O a - O)

Pn ~ImO tP r S o t NO.

10

Run X d e n t l f l - n a t i o n No.

223

222

221

155

154

158

156

7

69

9

14

64

30

31

32

44

36

38

39

40

46

45

47

50

53

m

~0

oo

tn

Col fig ]o.

5

] I

1 !

I ' a l [ M~ Q, H, C o . f i g d s g fl

6. - 6 . - 6 . - 6 - - 0 * N~ T~bs 4

~'~4- - 1 2 6o--b~--0

NO Tabs

~- - 6 - - - 1 2

'l'ab.~

1.02

l 1 . 0 4

1 . 0 0

0 . 6 8

0 , 7 0

0 . 7 2

0 . 8 0

0 . 8 0

0 . 9 0

- 1 . 0 , ) 0 0

1 . 0

0

- 1 . 0

0

0

1 . 0

1 . 0

1 . 0

0

0

1 . 0

1o0

0

1 . 0

- -1 .0

0

I

Table 2.

Py lon S t a t l o ,

S

Concluded

TER C o n f l g

S t a 1: M e t r i c S t a 2 , 3: Dummies

S t a 1: Empty S t a 2: M e t r i c S t a 3: Dummy

S t a 1: M e t r i c S t a 2 , 3 : Dummies

T r a J e c t o r y C o n d i t i o n

I n i t i a t e d f rom C a r r i a g e P o s i t i o n (ne e - o)

( n o R - - 4 0 )

( h e a - o)

( n e e - o)

I n i t i a t e d f r o m C a r r i a g e P o s i t i o n (nee - o)

I n i t i a t e d f rom C a r r i a g e P o s i t i o n ( n e e - o)

I n i t i a t e d from C a r r i a g e P o s i t i o n ( h e a = O)

(nO R = - l O )

(nee - - 2 0 )

(nee - -40)

P a r a m e t e r Run I d e n t i f i - -~et No. c a t x o n No.

10,

11

12

12

12

13

14

54

7 1 / 7 4

72

73

75

76

79

8 0 / 9 9

8 1

82

83

84

85

93

1 0 5 / 1 0 6

1 0 7 / 1 1 0

121

111

115

122

~> m 0 0

zl

~h

Con£ 1K No.

19

19

19

20

2O

20

21

21

21

22

22

22

23

23

23

94

T a l l C o n f l g

61-64- - -12

61:64---12

6 -6 - - 1 2 1 4 62-63-0

No Yabs

6 1 - 6 4 - - 1 2 6~-63-0

2 Tabs

6 1 - 6 4 - - 1 2 6~-63-0

Tabs 6 -6 - - 1 2 1 4 6 . -6~ -0 " 1;bg

6 1 - 6 a - - - 1 2 ai-6j-0

No Tabs

61-64---12 6i-6~-o No Tabs

6 : - 6 4 - - 1 2 ~ i - 6 3 - o

N o T a b e

61=64: -12 62-63-0

Tabs 61-64---12 6i-6~-0

Tabs 61 -64 - -12 6~-63-o

Tab8 6 -6 - - 1 2 1 4 62-65-0 No Tabs

61-64---12 6j:6 :. 6 1 - 6 4 - - 1 ] 6~-63-0 No Tab8

61-64- -12 6i-6~-o Tabs

Table 3.

0.50 6

0 . 7 0 4

0 . 9 0 2

0.50 6

0 . 7 0 4

0.90 2

0.50 6

0 . 7 0 4

0.90 2

0.50 6

0 . 7 0 4

0 . 9 0 2

0.50 6

0 . 7 0 4

0.90 2

0.50 6

Identification of Captive Trajectory Test Configurations with Test Conditions for A-7D Aircraft

H, P y l o n f t S t a t i o n

5 ,000 8

7

5,OOO

9

Py lon T r a j e c t o r y P a r a a e t e r Run I d e n t i f t - Congig C o n d i t i o n S e t No. c a t i o n No.

5ta 8: M e t r i c Sta 6, 7: I)ummles

S t a 7 : MetrAc 8 t a 6 : D i t t y 5 t a 8 : Empty

5ta 9: MetrAo 5 t a 7, 8: ] k p t y

I n i t i a t e d f rom C a r r l a s e P o s i t i o n

70

79

84

5

9

12

90

91

10"/

18

19

24

65

56

73

28

)> m O

3)

~J~

Co n f i K No.

24

24

25

25

25

20

26

20

27

27

27

28

28

28

29

29

T a i l ConfiK

6 _ - 6 _ - - 1 2 ,I-61-o

'JL~nb8

61-64 - - 1 2 6~-69-0

Tabs

6 1 - 6 4 - - 1 2

61-64 - --12 6i-6~-o

No Tabs

6 1 - 6 4 - --12 6.~-6~-o No Tabs

61 "64 " --12 62 -63 -0

Tab"

6 1 : 6 4 : - - 1 2 6~-6~-o

Tabs 6 . - 6 . - - 1 2 61-61-o

Tabs

b l - 6 4 - - - 1 2 6i-6~-0

No Tabs

61 -64 - - - 12 62-63-0 No Tabs

61-64 - --12

61-64 - - 1 2 6i-63-o

Tabs 6 1 - 6 A - - 12

61-64 - - 1 2 6 - - 6 - - 0 2 ~bs

6 1 - 6 4 - - 1 2

6 1 - 6 4 " --12

M~ deK

0 .70 4

0 .90 2

0 .50 6

0 . 2 0 4

0 .90 2

0 .50 5

0 . 7 0 4

0 . 9 0 2

0 .50 6

0 .70 4

0 . 9 0 2

0 . 0 0 5

0 .70 4

0 . 9 0 2

0 . 5 0 0

0 .70

It t ;

9 , ' DO

Table 3. Continued

Pylon Pylon T r a j e c t o r y P a r a m e t e r Run I d e n t i f i - S t a t i o n C o n f i l C e n d i t i o n Set No. c a t i o n No.

St& 0: M e t r i c 5 t a 7, 5= h p t y

S t a 0: M e t r i c 5 t a 7, 0: b p t y

S t a 1: M e t r i c S tn 2-6: DUamlns Py lon 1, 3: Empty

e t a I : I k p t y S t a 2: M e t r i c S t a 3 - 6 : Dummies Py lon I , 3 : [ k p t y

e t a I , 2: EMpty 5 t a 3 : N e t t l e 8 t a 4 -6 : ~ l e n Py lon 0 , S: ~ . .p ty

S t a 1, 2: Empty 9 t n 3: M e t r i c 5 t n 4 -0 : D u m l e e Py lon 6, S: ~ ' p t y

I n i t i a t e d from C a r r i a S e P o s i t i o n

I n i t i a t e d ~rom C a r r i a n e P o s i t i o n

33

29

77

80

83

4

0

14

] 03

104

I00

17

20

23

I I I

I12

m

31 zl

d

Conf ig N o ,

3O

50

50

31

51

51

52

32

52

33

33

33

34

34

34

T a l l ConfxK

61-64---12 6i-6~-o Tabs

6 . - 6 . - - 1 2 6 1 . 6 4 . 0 2 T~bs

61-64---12 6i-6;-o

Tabs

61-64--12 62-63-0 No Tabs

6 -6 - - 1 2 1 4 62-63-0 No Tabs

6 1 - 6 4 - - 1 2 6i-63-o

No Tabs 6 -6 - - 1 2 1 4 62-63-0

Tabs

61-64- - 12 6i-63-o

Tabs

61-64- -12 6,~-63-0

Tabs

61-64- -12

61-64- -12 62-63-0 No Tabs

61-64--12 " . m 6to' ; °.

61-64 - -12 6~-63-0

Tabs

6 1 - 6 4 - - 1 2 62-63-0

Tabs

61-64--12 6i-6~-0

Tabs

M~ de E

0.50 6

0.70 4

0.90 2

0.50 6

0.70 4

0.90 2

0.50 9

0 .70 4

0.90 2

0.50 6

0 .70 4

0.90 2

0.50 6

0 ,70 4

0 .90 2

Table 3. Continued

H, Py lon Pylon f t S t a t l o n Conf ig

5,000 Eta 1, 2: Empty Eta 3: Me t r i c Eta 4-6: Duu:ies Pylon 6, 8: Empty

Eta 1, 2: Empty Eta 3: M e t r i c E ta 4-6: Dummies Pylon 6, 8: Empty

Eta 1, 2: Empty Sta 3: Me t r i c Eta 4-6: Dummies Pylon 6, 8: Empty eta 1-3: Empty Eta 4: M e t r i c E ta 5, 6: Dmmles Py lon I . 3 : Empty

Eta 1-4= Empty eta 5: Me t r i c Eta 6: Dummy Pylon 6, 8: ~mpty

T r a 3 e c t o r y Cond i t ion

I n i t i a t e d from C a r r i a g e P o s i t i o n

Parameter Set No.


45

46

49

151

154

158

52

5S

57

152

153

158

53

54

58

m [J

-n

GO

~q 0~

C o n f • g No .

35

35

35

36

36

30

37

37

37

38

38

38

39

39

39

4O

T a L l C o n f i g

6 1 - 6 4 - - - 12 62-63-0

No T a b s

6 1 - 6 4 - - 12 6~-63-0 No Tabs

61-64- - 1 3 6jo6 . 61-64- --12 62-63-0

Tabs

6 - 6 - - 1 2 1 4 62-63-0

Tabs

61-64 - -12

6. - 6 4 - - 12 6~-63-0

NO T a b s

6 -64- - 12 621=63.0 No T a b s

61-64---12 6,]-63-0

No T a b s

61-64 - --12 62-63-0

Tabs

61-64- -- 12 62-63-0

'Tabs

6. - 6 . - - 12 • -8 62-63-0

Tabs

61-64- - 12 6.~-63-0

No T a b s

6 1 - 6 4 - -- 12 62-63-0 NO Tabs

61-64 - --12 62-63-0 No Tabs

6 1 - 6 4 - --12 62-63-0 No Tabs

Mq o

0.50

0 . 7 0

0.90

0.50

0 . 7 0

0.90

0.50

0 . 7 0

0.90

0.50

0 . 7 0

0.90

0.50

0 , 7 0

0.90

0,50

deK

S

4

2

S

4

2

6

4

2

5

4

2

5

4

2

6

~Jt

5 , )0

Table 3. Continued

P y l o n S t a t i o n

P y l o n C o n f l g

S t a 1 - S : Empty St& 6 : M e t r i c P y l o n 1, 3 : Empty

5 t a 1 : M e t r i c S t e 2 , 3 : D u l i e s P y l o n lp 3 : b p t y


I n i t i a t e d f r c m C a r r i a g e P o s i t i o n

P a r R ~ e t e r s e t No.


110

113

114

44

47

48

64

67

70

27

32

31

129

131

133

120

m o o

-n

co

Oil[£~ T a l l Nn, Confzg

614=6 - - 1 2 40 62=63-0

No Tabs

614=6 - - 1 2 40 62~63=0

No Tabs

61-64= - 1 2 41 62=63-0

Tabs

61-64- - 1 2 41 62-63-0

Tabs

61-~ 4- - 12 41 ~2-63-0

Tabs

42 61"62"63"~4"0 Tabs

42 61"62"63"64"0 Tabs

42 61"b2"63"~4"0 Tabs

61-64- -12 43 6~-63-0

No ' tabs

61=64- -12 43 ~ - 6 3 - 0

No Tabs

61=64- - 1 2 43 62-63-0

No Tabs

6 . - 6 4 - - 1 2 44 6~=63-0

Tabs

6 1 - 6 4 - - 12 44 62 -b3 -0

' tabs

~ i - 6 4 - - 1 2 44 ~ - 6 3 - 0

Tabs

6 -b2=63~64 . 0 45 I Tabs

45 61"62"~3"64"0 Tabs

45 61"62"63"64"0 Tabs

0 .70

0 .90

0 ,50

0 . 7 0

0 . 9 0

0 .50

0 .70

0 . 9 0

0 ,50

0 .70

0 . 9 0

O. 50

0 .70

0 .90

0 .50

0 . 7 0

0.90

deg..

4

2

6

4

2

6

4

2

6

4

2

6

4

2

6

4

2

II, f t

5,000

Table 3. Concluded

Pylon S t a t l o n

Pyton Conf lg

Sta 1: Fapty Sta 2: M e t r i c Sta 3: Dummy Pylon 6, R: ~ p t y

Sta 1, 2: Empty Sta 3: Me t r i c Pylon 1, 3: Empty

T r a j e c t o r y Cond i t i on

I n f t i a t e d f rom C a r r i a g o P o s i t i o n

P&rdmeCer ~ r t Ne.

Run I d e a L [ f i - r a t i o n NO

121

126

37

3H

41

144

145

148

119

122

123

39

39

40

143

146

147

m O c~

~0

0o

m

L~ oo

T a i l 61 C o n f l g

No 0 T a b s

I

L - 3

- 6

- 9

I

Table 4.

62 6 3

0 0

I 1 - 3 - 3

• ! i

- 6 - 6

I i !

- 9 - 9

6 4

0

- 3

I |

- 6

1 - 9

Identification of Static Stability Test Conditions for the O.05~Scale MVB Model

Moo

0 . 5 0

0 . 7 0

0 . 9 0

1 . 1 0

0 . 5 0

0 . 7 0

0 . 9 0

1 . 1 0

0 . 5 0

0 . 7 0

O.9O

1 . 1 0

0 . 5 0

0 . 7 0

0 . 9 0

1 . 1 0

Cfp

deg

- 2 0 t o 20

F i n Fuze F i n Gap H i n g e L i n e

None None

R u n I n d e n t t f i c a t t o n

N o .

91

95

9 6

9 8

102

103

104

105

108

109

I I 0

I I I

114

118

121

124

m o

~0

00

Table 4. Continued

T a t l C o n f i g

N o

T a b s

61 62 63 6 4

- 1 2 - 1 2 - 1 2

T a b s

- 6

- 9

I

- z 2 I

Moo

- 1 2 0 . 5 0

, 0 . 7 0 i

! 0 . 9 0

I I . I 0

0 0 0 . 5 0

0 . 7 0

0 . 9 0

" I . I 0

- 6 0 . 5 0

0 . 7 0

l o . 9 o ;

z . lO

- 9 O. 50

0 . 7 0

0 . 9 0

1 . 1 0

" - 1 2 0 . 5 0

(IF w

deg

- 2 0 t o 20

- 3 0 t o 30

F i n H i n g e L i n e

F u z e

N o n e

F i n Gap

None

Run I n d e n t t f l c a t i o n

No.

128

133

134

136

19

21

25

26

32

33

34

36

40

41

42

43

3

m

o

-n

CO

Q

T a i l C o n f i g

T a b s

T a b s

T a b s

No T a b s

T a b s

T a b s

61

- 1 2

,p

o

0

0

- 1 2

62

0

6 3 6 4 Moo

0 - ] 2 0 . 7 0

0 . 9 0

1 . I 0

0 . 5 0

0 . 7 0

0 . 9 0

0 . 5 0

0 . 7 0

0 . 9 0

0 0 . 7 0

0 0 . 9 0

0 1 . 0 2

- 1 2 0 . 7 0

! i 0 . 9 0

0 . 7 0

" ,r 0 . 9 0

Table 4. Concluded

Run a , F i n F u z e F i n I n d e n t i f i c a t i o n

d e g H i n g e L i n e Gap No .

5 N o n e N o n e - 3 0 t o 3 0

- 3 0 t o 3 0

- 3 0 t o 3 0

- 3 0 t o 3 0

+4 t o - 5 2

+ 4 t o - 4 4

+4 t o - 4 4

+4 t o - 5 2 / - 4 t o +56

+4 t o - 3 6 / - 4 t o 44

+4 t o - 5 2 / - 4 t o 52

4 t o - 3 2 / +4 t o - 3 6

~r

FMU-56

Yes

4

5

7

2 5 2

253

2 5 4

2 4 7

248

2 4 9

149

1 5 0

151

1 4 1 / 1 4 5

1 4 2 / 1 4 6

1 3 2 / 1 3 7

1 3 4 / 1 3 8

m

f~

O0

. o

i Table 5. Identification of Static Stability Test Conditions for the 0.25-Scale MVB Model

Tall C o n f i g

Tabs

No Tabs

Tabs

61

0

6 2

0

5 3

0

5 4 M~ deg deg

0.50

0.50

0 . 7 0

0 . 7 0

0 . 9 0

O.9O

0 . 9 0

1 . 1 0

1 . 1 0

0 . 5 0

0 . 7 0

0 . 9 0

1 . 1 0

0 . 5 0

0.70

0.90

l .10

0 . 5 0

- 6 to 26

0

180

0

180

0

0

180

0

180

Fin Hinge Line

Fuze

None

FMU-56

Fin Gap

Yes

None

Rue I n d e n t i f t c a t i o n

No.

13

14

15

16

17

18

19

20

21

32

33

34

35

38

39

4O

41

44 I T I

O o

-.n

0 0

rj~ 63

Table 5. Continued

T a i l 6. 6 C o n f l g _

T a b s 0

0

0

- 1 2

6. I 6

- 1 2

N o T a b s

1 No

F i n s

N o F i n s

No F i n s

i i

! i

~p [ M~ d e g

- 6 ) 0 . 7 0 t o

26

) 0 . 9 0

} ] . 1 0

0 . 5 0

0 . 7 0

0 . 9 0

1 . 1 0

0 . 5 0

0 . 7 0

0 . 9 0

1 . 1 0

0 . 5 0

0 . 7 0

0 . 9 0

1 . 1 0

0 . 5 0

0 . 7 0

0 . 9 0

~ t d e g

0

0

0

O, 1 8 0


F u z e

F M U - 5 6

N o n e

F1 n GI p

Nc n e

R u n I n d e n t i f i c a t i o n

N o .

4 5

4 6

4 7

5 0

51

52

55

58

59

60

6 I

6 4

6 5

66

69

72

7 3

7 4

m

c~

"n

GO

Table 5. Continued

Ta~t C o n f x g

No F f n s

T a b s

- ' 2

6

- 2

1 .10

0 .50

0 .50

O. 70

0 .70

0 .90

0 ,90

I . I 0

1 .10

0 .50

0 .50

0 . 7 0

0 . 7 O

0 . 9 0

o. 90

1 . 1 0

1 . 1 0

0 .50

L~

deg

- 6 t o 26

~v

d e g

0

O, 180

45 , - 1 3 5

0 180

4 5 . - 1 3 5

O, 180

4 5 . - 1 3 5

O, 180

45 , - 1 3 5

O, 180

90 , - 9 0

O. 180

9 0 , - 9 0

O, 180

9 0 , - 9 0

O, 180

9 0 , - 9 0

O, 180

F i n F u z e I I I nge L i n e

None

FMU-56

Nonc

F i n Gap

None I R u ~

I n d e n t i f i c a t t o n No.

75

78

79

80

81

82

83

84

85

88

89

90

91

92

93

94

95

98

~> m o f~

~o

O0 J~

m

o~ 4~

T a i l C o n f i g

T a b s

T a b s

T a b s

No Tabs

61

-12

-12

- 1 2

0

6 2

Table 5. Continued

6 3 6 4 M~ a, ~, deg d e g

0 0 - 1 2 0 . 7 0 - 6 t o 26

. l O

. 5 0

.50 ,

. 7 0

. 7 0 i

. 9 0 !

. 9 0 i

. 1 0 '

- 1 2 0 . 9 0

- 1 2 I . I 0

0 0 . 5 0

0 . 5 0

0 . 7 0

0 . 7 0

J 0 . 9 0

I 0 . 9 0

I . I 0

[ 1 ;

0

0

0 ; 0

0

0

0 t

180

O, 180

O, 180

0

45

0

45

0

45

0

45

0

45

0

45

0

45

0


5

F u s e

N o n e

None

None

FMU-56

None

F i n Gap

Yes

Run I n d e n t t f t c a t t o n

N o .

9 9

104

105

108

109

110

111

112

113

118

119

122

125

126

127

128

129

130

m o o

:D

Table 5. Continued

m

T a i l C o n f i g

N o T a b s

61

0

-12

6 2 6 3 6 4

0

-12

1 I i

1 1

I -I

l

Moo

1 . 1 0

0.50

0 .50

0 .70

0 . 7 0

0 . 9 0

0 . 9 0

1 . 1 0

1 . 1 0

0.50

0 .50

0 .50

0 ,70

0 . 7 0

0 . 7 0

0.90

0 . 9 0

0 . 9 0

d e g d e g

- 6 t o 26

45

0

180

0

180

0

180

0

180

0, 180

45, - 135

90, - 9 0

0, 180

45, -135

90, - 9 0

0, 180

45, - 135

90, - 9 0


F u z e

None

FMU--56

F l n Gap

Yes

I i

!

I

I I I

J,

R U b

I n d e n t l f t c a t l o n N o .

131

134

135

136

137

138

139

140

141

144

145

146

147

148

149

1 5 0

1 5 1

1 5 2

I1'1 (3 O

-n

¢0 J~

m . ,

o~ o~

Table 5. Continued

T a i l 61 62 63 54 M~ a , C o n f i g deg

NO Tabs

- 1 2

! I

0 0 - 1 2

0 0

0 0

- 1 2 - 1 2

1 . 1 0

1 . 1 0

1 . 1 0

0 . 5 0

0 . 7 0

0 . 9 0

1 . 1 0

0 . 5 0

0 . 7 0

0 . 9 0

1 . 1 0

0.50

0 . 7 0

0 . 9 0

1 . 1 0

1 . 1 0

0.50

0 . 7 0

Tabs

- 6 t o 26

~P deg

Op 180

45, -135

90, - 9 0

O, 180

O, 180

180

0

O, 180

O, 180

F i n H i n g e L i n e Fuze

FMU-56

None

FMU-56

FMU-56

F i n Gap

Yes

Run I n d e n t t f t c a t l o n

No.

153

154

155

158

159

160

161

164

165

169

167

170

171

172

173

174

177

178

m o

:D

G)

Tail Conl ig

Tabs

61

- 1 2

T a b s F a i r e d

I n

! i l

i I i

N o T a b s

- 1 2 - 1 2 - 1 2

b 2 6 3 6 4 .'d,~

-12 -12

0 0

I

i

1.90

.10

I 0.50

0.70

0.90

I .I0

0.50 t

0.70

0.90

1 . I 0

0.50

0 . 5 0

0 . 7 0

0 . 7 0

0 . 9 0

0 . 9 0

1 . 1 0

1 . 1 0

0 . 5 0

0 . 5 0

0 . 7 0

0 . 7 0

0 . 9 0

Table 5. Concluded

dog

[to 25

. o

~, F i n d e g H i n g e L i n e

Or

180

l

I

0

r

45

0

45

0

45

0

45

0

45

0

45

0

F u z e

5 FMU-56

FMU-56

FMU-LI0

FMU-56

!

None

,p

F i n Gap

Yes

I

~p

N o n e

Ru n I n d e n t i f i c a t i o n

N o .

179

180

183

188

189

190

197

198

199

2O0

203

204

205

206

207

208

209

210

213

214

215

216

217

m

o

~o

co

OO

Table 6. Dynamic Stability Test Configurations and Test Conditions for the 0.075-Scale MVB Model

Config

1

1

1

2

2

2

1

2

3

4

4

~ , d e g

0 - ~ 4 5

0 -P -45

- 4 5 - ~ 4 5

0 - ~ 4 5

- 5 - ~ 4 5

- 4 5 - ~ 4 5

- 4 5 - ~ 4 5

- 4 5 - ~ - 4 5

- 5 - " 4 5

- 5 - ~ 4 5

- 4 5 - ~ 4 5

~ , d e g 51 5 2

0

45

0

0

45

0

0

0

-12

0

0

-12

-12

-12

0

-12

0

-12

-12

0

0

6 3

- 1 2

- 1 2

6 4

0

0

-12

0

0

-12

-12

-12

0

- 1 2

0 . 5 0

3

14

19

30

35

46

51

65

70

81

86

Mach N o .

0 . 7 0 0 . 9 0

4 5

13 12

2 0 21

29 28

3 6 37

4 5 44

52 53

6 4 63

71 72

8 0 79

87 88

1 . 1 0

6

11

22

27

38

43

54, 57

62

73

78

89

> m

Configuration

1

2

3

4

D e s c r i p t i o n

B o d y + F i n s + FMU-56 F u z e

B o d y + F i n s + FMU-56 F u z e + T a b s

B o d y A l o n e

B o d y + F i n s

A EDC-TR-78-4

/

Table 7. Typical Uncertainties for Force and Moment Coefficient Data and Trajectory Data

F o r c e and Moment C o e f f i c i e n t D a t a

6% 6% 6c A

_+0.08 _+0.04 _+0.02

6C m

± 0 . 0 4

6C n

±0.04

Captive Trajectory Data

t , s e c 5Xp

0 . 2 + 0 . 0 2

6~

+0.01

6Zp

_+0. 003

60

_+0.20

6~

+ 0 . 1 0

169

A I: D C-T R -7 8 -4

BL

b

CA

C~p

Cm

Cm a

Cm q

Crn a

CN

CN a

Cn

Cn

Cv

FS

Fz i

Fz 2

H

H.L.

lxx

Ixz

NOMENCLATURE

Aircraft buttock line from plane of symmetry, in., model scale

Store reference dimension, It, full scale

Store axial-force coefficient, axial force/q**S

Store rolling-moment coefficient, rolling moment/q=.Sb

Store roll-damping derivative, dC£/d(pb/2V**)

Store pitching-moment coefficient, referenced to the store moment/q=Sb

Rate of change of Cm with angle of attack, per radian

Store pitch-damping derivative, acre/a(qb]2V=)

Store pitch-damping derivative, acre/a(~b/2V=)

Store normal-force coefficient, normal force/q**S

Rate of change of CN with angle of attack, per radian

Store yawing-moment coefficient, referenced to the store moment/q=Sb

Store yaw-damping derivative, dCn/d(rb/2V=)

Store side-force coefficient, side force/q=S

Aircraft fuselage station, in., model scale

Forward ejector force, lb

Aft ejector force, lb.

Pressure altitude, ft

Fin hinge line

Full-scale moment of inertia about the store X~ axis, slug-ft 2

Full-scale product of inertia in the store Xt~ - ZB plane, slug-ft 2

cg,

cg,

pitching

yawing

170

lyy

[z~

M®

m

P

P=

q

q=

Red

r

S

t

v

WL

Xe

Xeg

XL 1

XL 2

XN P

Yp

ZE

A E DC-TR-78-4

Full-scale moment of inertia about the store Ys axis, slug-ft 2

Full-scale moment of inertia about the store Zu axis, slug-ft 2

Free-stream Mach number

Full-scale store mass, slugs

Store angular velocity about the XB axis, radians/sec

Free-stream static pressure, psfa

Store angular velocity about the YB axis, radians/sec

Free-stream dynamic pressure, psf

Reynolds number based on model diameter

Store angular velocity about the Zs axis, radians/sec

Store reference area, ft 2, full scale

Real trajectory time from initiation of trajectory, see

Free-stream velocity, ft/sec

Aircraft waterline from reference horizontal plane, irr., model scale

Separation distance of the store cg: parallel to the...pylon axis_system Xp direction, ft, full scale mea_~Esured from the_pselaunch position

Full-scale cg location, ft, from nose of store

Forward ejector location relative to the store cg, positive forward of store cg, ft, full scale

Aft ejector location relative to the store cg, positive forward of store cg, ft, full scale

Neutral point location, Xcg -(Cma/CNa)b, in.

Separation distance of the store cg. para]_lel _t.o the pylon, a_xis system Yp direction, ft,_f_ull scale measured from the pr.ela_u.n_~ch position

Ejector stroke, ft

171

A E D C-TR -78-4

Z o, Initial offset of store from carriage position, ft, full scale

Zp Separation distance of the store cg parallel to the pylon-axis system. Zp direction, ft, full scale measured from the prelaunch position

a Aircraft model angle of attack relative to the free-stream velocity vector, deg

d Time rate of change of angle of attack, radians/sec

as Store model angle of attack relative to the free-stream velocity vector, deg

8 Fin deflection angle, deg

A0 Angle between the store longitudinal axis and its projection in the Xp-Yp plane, positive when store nose is raised as seen by the pilot, deg

I L

A~ Angle between the projection of the store longitudinal axis in the Xp-Yp plane and the Xp axis, positive when the store nose is to the right as seen by the pilot, deg

A~ Angle between the store lateral axis and the intersection of the YB-ZB and Xp-Yp planes, positive for clockwise rotation when looking upstream, deg

AOR Angle at which store is released from pivotal motion, deg

FLIGHT-AXIS SYSTEM COORDINATES

Directions

XF Parallel to the free-stream wind vector, positive direction is forward as seen by the pilot

YF Perpendicular to the Xr and ZF directions, positive direction is to the right as seen by the pilot

Z~ in the aircraft plane of symmetry and perpendicular to the free-stream wind vector, positive direction is downward

The flight-axis system origin is coincident with the aircraft cg and remains fixed with respect to the aircraft during store separation. The XF, YF, and ZF coordinate axes do not rotate with respect to the initial flight direction and attitude.

172

AE DC-TR-78-4

STORE BODY-AXIS SYSTEM COORDINATES

Directions

XB Parallel to the store longitudinal axis, positive direction is upstream in the prelaunch position

Ys Perpendicular to the store longitudinal axis, and parallel to the flight-axis system XF-YF plane ~vhen the store is at zero roll angle, positive direction is to the right looking upstream when the store is at zero yaw and roll angles

Zs Perpendicular to both the XB and Ys axes, positive direction is downward as seen by the pilot when the store is at zero pitch and roll angles

The store body-axis system origin is coincident with the store cg and moves with the store during separation from the airplane. The XB, YB, and ZB coordinate axes rotate with the store in pitch, yaw, and roll so that mass moments of inertia about the three axes are not time-varying quantities.

PYLON-AXIS SYSTEM COORDINATES

Directions

Xp Parallel to the store longitudinal axis when in the carriage position on the aircraft, positive direction is forward as seen by the pilot

Yp Perpendicular to the Xp axis and parallel to the flight-axis system XF-YF plane, positive direction is to the right as seen by the pilot

Zp Perpendicular to both the Xp and Yp axes, positive direction is downward

The pylon-axis system origin is coincident with the store cg in the prelaunch carriage position. The axes are rotated with respect to the flight-axis system by the prelaunch yaw and pitch angles of the store. Both the origin and the direction of the coordinate axes remain fixed with respect to the flight-axis system throughout the trajectory or survey.

173

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