i m

I

I

AEDC-TR-69-98 ARCHIVE COPY DO NOT LOAN

AEROELASTIC STABILITY TESTS OF THIN CYLINDRICAL SHELLS AT

SUPERSONIC SPEEDS (FOLLOW-ON TESTS)

Oo.~ ~.

% %

Warren E. White

ARO, Inc.

This document has b,~en appro¢-~d ;:or public release . . . . it~ d:-tribut!on is u~li.m. ;t,-.-d. ~O, ,~ . -~ . f "J " ) ' L " ~ ,

April 1969 " ~ d . / 0,3., 9L.

~ ' ~ m e n t is s u b j e c t ~ l export controls/ /~nd each ~ansmittal to f~ign govec]~ents or foreig)/ r nationals n~y be mad•only with prl~r approval/~f

Air. Force ~ffice of/Sc'enll ific Rese~ch (S~M), /Arlington, Vir "nia

PROPULSION WIND TUNNEL FACILITY

ARNOLD ENGINEERING DEVELOPMENT CENTER

AIR FORCE SYSTEMS COMMAND

ARNOLD AIR FORCE STATION, TENNESSEE

. . [ . . . . . . . . . - , . , - - - - [. , _ 2 ~ , ' C , ; ( ' ? ,

~,. 5,,,j~, :... C; .-- C .-. 000~,

NOTICEX When U. S. Government drawings speci f ica t ions , or other data are used for any purpose other than a def ini te ly related Government procurement operation, the Government thereby incurs no responsibi l i ty nor any obligation whatsoever, and the fact that the Government may have formulated, furnished, or in any" way supplied the said d r a w i n g , spec i f ica t ions , or other data, is not to be regarded by implication or otherwise, or in any manner l icens ing the holder or any other person or corporation, or conveying any rights or permission to manufacture, use, or se l l any patented invention that may in any way be related thereto.

Qualif ied users may obtain copies of this report from tile Defense Documentation Center.

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

AE DC-TR-69.98

AEROELASTIC STABILITY TESTS OF

THIN CYLINDRICAL SHELLS AT

SUPERSONIC SPEEDS

(FOLLOW-ON TESTS)

War ren E. White

ARO, Inc.

This document has 10een approved for. [F;.U_.I_g.L~.71..t,. h R u b l i . . c rete~as.,e_ ,,'J • " its distribution is unlimited. ~

. . . . - . . ~ - , ~ Io~.,-/L.

Thisfil~'eu'~nt is subject/~o"sp~ial export contro~ and/each trallsmittal toJ~reign governments or forf~gn n~o~.l~ m~°.be m~e only with ~rior appro~l of I~/ F:::? V~2~ientifi. ff~B E'v|),

AEDC.T R-69-98

FOREWORD

The work r epo r t ed h e r e i n was done at the r eques t of the A e r o s p a c e E n g i n e e r i n g Depa r tmen t of the U n i v e r s i t y of Texas for the Ai r F o r c e Office of Scient i f ic R e s e a r c h (AFOSR), Ai r F o r c e S y s t e m s Command (AFSC}, under P r o g r a m E lemen t 61102F, P r o j e c t 9782.

The r e s u l t s of the tes t p r e s e n t e d were obtained by ARO, Inc. (a sub- s i d i a r y of Sve rd rup & P a r c e l and A s s o c i a t e s , Inc. ), con t r ac t ope ra to r of the Arnold E n g i n e e r i n g Development Cen te r (AEDC), AFSC, Arnold A i r F o r c e Station, T e n n e s s e e , under Cont rac t F40600-69-0001. The t e s t was conducted f rom J a n u a r y 7 th rough 20, 1969, under ARO P r o j e c t No. PS0931. The m a n u s c r i p t was submi t t ed for publ ica t ion on Apr i l 2, 1969.

In fo rma t ion in th i s r epor t is e m b a r g o e d under the D e p a r t m e n t of State In t e rna t i ona l Tra f f i c in A r m s Regula t ions . This r epo r t may be r e l e a s e d to fo re ign g o v e r n m e n t s by d e p a r t m e n t s or agenc i e s of the U. S. Governmen t subject to approva l of the Ai r F o r c e Office of Scient i f ic R e s e a r c h (SREM), or h ighe r au tho r i t y within the Depar t - ment of the Ai r F o r c e . P r i v a t e ind iv idua ls or f i r m s r e q u i r e a Depar t - ment of State expor t l i c ense .

This technical report has been reviewed and is approved.

Richard W. Bradley Lt Colonel, USAF AF Representative, Directorate of Test

PWT

Roy R. troy, Jr. Colonel, USAF Director of Test

i i

A E D C-T R-69.98

ABSTRACT

F o l l o w - o n t e s t s to an i n v e s t i g a t i o n to d e t e r m i n e the d y n a m i c c h a r - a c t e r i s t i c s of th in c y l i n d r i c a l s h e l l s w e r e c o n d u c t e d in the P r o p u l s i o n Wind T unne l , S u p e r s o n i c (16S}. T h e m o d e l c o n s i s t e d of an og ive c y l i n d e r wi th the t e s t s h e l l l o c a t e d on the c y l i n d r i c a l p o r t i o n of the m o d e l a p p r o x i m a t e l y 78 p e r c e n t of the m o d e l l e n g t h aft of the n o s e . Da ta w e r e r e c o r d e d at M a c h n u m b e r s of 2 . 2 and 2 . 5 for 0 - d e g a n g l e of a t t a c k and yaw. F l u t t e r was i nduced on the 0. 0020- and 0. 0032- in . - t h i c k s h e l l s by r e d u c i n g the m o d e l c av i t y p r e s s u r e . B o u n d a r y - l a y e r m e a s u r e m e n t s w e r e a l s o m a d e at v a r i o u s b o u n d a r y - l a y e r b lowing r a t e s .

This document has been approved ;or.~ublic re lea~ -.~ -~ ..Iq • " ' - " ' j

its distribution is unlimited. I ~ " ' " " 'L .

This ~ e n t is s u b j e c ~ l export controls andy~eh trdllsmittal to,~6reign govel~nments or f o ~ " n~_ ona~ m~y be m~re only _.with ~ior appr~al of

"" 22209.

~o

iii

AEDC.TR.69.98

CONTENTS

ABSTRACT . . . . . . . . . . . . . . . . . . . . .

N O M E N C L A T U R E . . . . . . . . . . . . . . . . . . .

I. INTRODUCTION . . . . . . . . . . . . . . . . . . . .

If. APPARATUS

2. 1 Wind Tunnel . . . . . . . . . . . . . . . . . . .

2.2 Test Article . . . . . . . . . . . . . . . . . .

Ill. TEST DESCRIPTION

3. 1 Test Procedure . . . . . . . . . . . . . . . . . .

3.2 Instrumentation . . . . . . . . . . . . . . . . . .

3.3 Precision of Measurements . . . . . . . . . . . . .

IV. RESULTS AND DISCUSSION . . . . . . . . . . . . . .

REFERENCES . . . . . . . . . . . . . . . . . . . .

Page

iii

vi

1

2 3 3 4 4

TABLE

I. S u m m a r y of T e s t I n f o r m a t i o n . . . . . . . . . . . . . .

APPENDIX Illustrations

F i g u r e

1. S k e t c h of t h e M o d e l in t h e Tun.nel 16S T e s t S e c t i o n .

2. P h o t o g r a p h of t h e M o d e l I n s t a l l e d in t h e T u n n e l 16S T e s t S e c t i o n . . . . . . . . . . . . . . . . . . . .

3. M o d e l D i m e n s i o n s a n d D e t a i l s . . . . . . . . . . . .

4. D e t a i l s of t h e T e s t P a n e l . . . . . . . . . . . . . . .

5. D e t a i l s of t he B o u n d a r y - L a y e r R a k e s . . . . . . . . .

6. S k e t c h of t h e T r a v e r s i n g R a k e ( R a k e 3) . . . . . . .

7. L o c a l M a c h N u m b e r P r o f i l e s as a F u n c t i o n of A u x i l i a r y

B o u n d a r y - L a y e r W e i g h t F l o w , 4v, at x / L = 0 . 9 7 , M® =2.2

a. Pt® = 325 psf, Re/ft = 0.496 x 106 . . . . . .

b. Pt® = 400psf, Re/ft = 0.598 x 106 . . . . . . .

9

10

11

12

13

14

15

16

V

AE DC.TR.69.98

F i g u r e

8. L o c a l Mach N u m b e r P r o f i l e s with and wi thout A u x i l i a r y B o u n d a r y - L a y e r Weight "Flow, ~v, at She l l S ta t ions x / L f r o m 0 t o 0 .97 , M® = 2 .2 , lot® = 4 0 0 p s f , R e / f t = 0 .598 x 106 . . . . . . . . . . . . . . . . .

Pag____e

17

NOMENCLATURE

D

E

F

h

L

ML

M®

P

Pc

Pt® q®

R

R e / f t

v®

;v

X

Y

A.p c v®

Model r e f e r e n c e d i a m e t e r , 1. 333 ft

Young ' s modu lus of e l a s t i c i t y ,

F l u t t e r p a r a m e t e r ,

2. 736 x 109 , ps f

/ q® / 1/3

E M 2 - 1 h

1. 333 ft

She l l t h i c k n e s s , in.

She l l r e f e r e n c e length ,

L o c a l Mach n u m b e r

F r e e - s t r e a m Mach n u m b e r

P r e s s u r e m e a s u r e d on the m o d e l s u r f a c e d o w n s t r e a m of the t e s t she l l , p s i

Cav i ty p r e s s u r e be ne a t h the she l l , p s i

F r e e - s t r e a m to t a l p r e s s u r e , ps f

F r e e - s t r e a m d y n a m i c p r e s s u r e , psf

She l l r a d i u s , 8 .00 in.

V® R e yno lds n u m b e r p e r foot, v---~

F r e e - s t r e a m ve loc i t y , f t / s e c

Weight flow into b o u n d a r y l a y e r , l b / s e c

D i s t a n c e f r o m the f o r w a r d edge of the t e s t she l l , ft

D i s t a n c e m e a s u r e d n o r m a l to the m o d e l s u r f a c e , in.

D i f f e r e n t i a l p r e s s u r e a c r o s s the she l l , (Pc - p}' p s i

F r e e - s t r e a m k i n e m a t i c v i s c o s i t y , f t 2 / s e c

R o t a t i o n a l ang le m e a s u r e d on the m o d e l (F ig . 4), deg

vi

A E D C-T R.69.98

SECTION I

INTRODUCTION

The f o l l o w - o n t e s t s to the c y l i n d r i c a l s h e l l f l u t t e r p r o g r a m r e p o r t e d h e r e i n w e r e done at the r e q u e s t of the A e r o s p a c e E n g i n e e r i n g D e p a r t - m e n t of the U n i v e r s i t y of T e x a s , Aus t in , T e x a s . T h e t e s t was c o n d u c t e d on an og ive c y l i n d e r m o d e l in the P r o p u l s i o n Wind Tunne l , S u p e r s o n i c (16S) at 0 - d e g ang le of a t t a c k and at .'~lach n u m b e r s of 2 .2 and 2 .5 . The p u r p o s e of the t e s t was to d e t e r m i n e the e f f ec t s of b o u n d a r y - l a y e r c h a r - a c t e r i s t i c s wi th c o n t r o l l e d b o u n d a r y - l a y e r b lowing on the d y n a m i c be - h a v i o r of the s h e l l .

The r e l a t e d t e s t s a r e c o v e r e d in Re f s . I and 2 w h i c h p r e s e n t s t a t i c p r e s s u r e d i s t r i b u t i o n s , b o u n d a r y - l a y e r p r o f i l e s , and s h e l l f l u t t e r da t a fo r M a c h n u m b e r s f r o m 1 .20 to 3 .0 .

SECTION II

APPARATUS

2.1 WIND TUNNEL

T u n n e l 16S is a v a r i a b l e d e n s i t y wind t unne l c a p a b l e of o p e r a t i n g at M a c h n u m b e r s f r o m I. 5 to 4 .75 . The t e s t s e c t i o n is 16 ft s q u a r e and is c o m p o s e d of two 2 0 - f t - l o n g r e m o v a b l e s e c t i o n s . A m o r e c o m p l e t e d e s c r i p t i o n of the t u n n e l m a y be found in Ref. 3, and c a l i b r a t i o n r e s u l t s a r e p r e s e n t e d in Ref . 4. A s k e t c h of the m o d e l i n s t a l l e d in the t e s t s e c t i o n is p r e s e n t e d in F ig . I, and a p h o t o g r a p h of the m o d e l is p r e - s e n t e d in F ig . 2.

2.2 TEST ARTICLE

The g e o m e t r y of the c y l i n d r i c a l s h e l l m o d e l is p r e s e n t e d in F i g s . 3 and 4. A d d i t i o n a l s h e l l s of t h i c k n e s s e s f r o m 0. 002 to 0. 004 in. w e r e supp l i ed , and an a u x i l i a r y b o u n d a r y - l a y e r b l e e d was i n c o r p o r a t e d in the m o d e l s i n c e the p r e v i o u s t e s t s . T h e a u x i l i a r y b l eed was i n c o r p o r a t e d n e a r the end of th is t e s t and c o n s i s t e d of 0. 063- in . ho l e s 0 .5 in. a p a r t d r i l l e d into the ax ia l b l a d d e r and d i r e c t e d t o w a r d the s u r f a c e 90 deg to the a i r s t r e a m . Th i s p e r m i t t e d a d i f fus ive b lowing in to the b o u n d a r y l a y e r i m m e d i a t e l y u p s t r e a m of the t e s t s h e l l .

The t e s t s h e l l i t s e l f was a r i g h t - c i r c u l a r c y l i n d e r 16 in. in d i a m e t e r and 16 in. long and began 96 in. aft of the m o d e l nose and 48 in. aft of

A EDC.TR.69.98

the beg inn ing of the c y l i n d r i c a l p o r t i o n of the m o d e l . The t h i c k n e s s e s of the s h e l l s w e r e 0. 0020, 0 .0032 , and 0. 0040 in. The p r e s s u r e d i f f e r - e n t i a l a c r o s s the s h e l l was c o n t r o l l e d by v a r y i n g the i n t e r n a l p r e s s u r e . H i g h - p r e s s u r e r u b b e r b l a d d e r s w e r e u s e d to s e a l the i n t e r n a l c a v i t y and p r e v e n t p r e s s u r e l o s s . Ax ia l l oad ing on the s h e l l cou ld be app l i ed by in f l a t ing a b l a d d e r wh ich a c t e d on the f o r w a r d - e n d r i n g of the s h e l l . Th i s b l a d d e r was l a t e r u s e d for the a u x i l i a r y b o u n d a r y - l a y e r b l eed . A m o r e d e t a i l e d d e s c r i p t i o n of the m o d e l m a y be found in Ref . 2.

T h r e e r a k e s w e r e u s e d to m e a s u r e the b o u n d a r y - l a y e r p r o f i l e s . R a k e 1 was a d j u s t a b l e in he igh t and m o u n t e d at $ = 33 deg; w h e r e a s , r a k e 2 was f ixed and m o u n t e d at 147 deg. R a k e s 1 and 2 w e r e l o c a t e d 0 .5 in. f o r w a r d of the aft edge of the s h e l l . Rake 3 was u s e d to i n v e s t i - ga t e the b o u n d a r y - l a y e r g r o w t h f r o m the b lowing s lo t and a u x i l i a r y b low- ing p o s i t i o n to the aft p o r t i o n of the t e s t s h e l l by t r a v e r s i n g the d i s t a n c e iri f in i te s t e p s .

SECTION III TEST DESCRIPTION

3.1 TEST PROCEDURE

T h e t e s t was c o n d u c t e d at M a c h n u m b e r s of 2 .2 and 2 .5 fo r a n g l e s of a t t a c k and yaw of 0 deg. D y n a m i c da ta w e r e t ape r e c o r d e d con - t i n u o u s l y ; w h e r e a s , the s t e a d y - s t a t e da t a w e r e a c q u i r e d d u r i n g b o u n d a r y - l a y e r s tudy and p a u s e s d u r i n g f l u t t e r and buck l ing s e a r c h . A s u m m a r y of the f l u t t e r r e s u l t s is g iven be low in T a b l e I. F l u t t e r and b u c k l i n g c h a r a c t e r i s t i c s w e r e o b t a i n e d at a M a c h n u m b e r of 2 .2 only . T e s t c o n - d i t i ons w e r e e s t a b l i s h e d i n i t i a l l y at a low d y n a m i c p r e s s u r e . The d y n a m i c p r e s s u r e was then s l o w l y i n c r e a s e d unt i l a d e s i g n a t e d i n c r e - m e n t was r e a c h e d , at wh ich t i m e i n t e r n a l p r e s s u r e and s h e l l ax ia l l o a d - ing w e r e v a r i e d to i nduce f l u t t e r o r buck l ing .

TABLE I SUMMARY OF TEST INFORMATION

Pt®, q=0 ~Pc' (v, IV[® psi psi Re/it, x 10 -6 1~ psi h, in. lb/sec Remarks

2.2 988 313 1. 465 10.7 0.64 0.0032 0 Zero axial loading

2.2 350 III 0. 543 12. 1 0.24 0. 0020 0 Zero axial loading

A EDC.TR.69-98

B o u n d a r y - l a y e r p r o f i l e data w e r e ob ta ined f r o m the t h r e e r a k e s at s e v e r a l b o u n d a r y - l a y e r b lowing r a t e s and at s e v e r a l t unne l p r e s s u r e s .

3.2 INSTRUMENTATION

T w e n t y - n i n e to ta l p r e s s u r e s w e r e m e a s u r e d f r o m the t h r e e b o u n d a r y - l a y e r r a k e s (F ig s . 5 and 6), and a s t a t i c r e f e r e n c e p r e s s u r e was m e a s u r e d on the m o d e l s u r f a c e . P r e s s u r e m e a s u r e m e n t s i n s i d e the s e a l i n g ( r ad ia l ) b l a d d e r s and the load ing (axial) b l a d d e r w e r e r e - c o r d e d , as w e r e p r e s s u r e s wi th in the b o u n d a r y - l a y e r b lowing s y s t e m and the m o d e l cav i ty r e g i o n .

T h r e e m u t u a l i n d u c t a n c e p r o x i m i t y s e n s o r s w e r e u sed to m o n i t o r the s t a t i c and d y n a m i c d i s p l a c e m e n t of the s h e l l s . The s e n s o r s o p e r - a t ed without c o n t a c t i n g the s h e l l s u r f a c e with m a x i m u m output of a p p r o x i m a t e l y 4 v o c c u r r i n g when the s h e l l s u r f a c e was fa r away. The output d e c r e a s e d as the m e t a l s k i n n e a r e d the s e n s o r head . One of the t h r e e s e n s o r s could be p o s i t i o n e d l ong i t ud ina l l y and c i r c u m f e r e n t i a l l y , a s e c o n d could be p o s i t i o n e d l o n g i t u d i n a l l y only, and the t h i r d was f ixed. The s i g n a l s f r o m the s e n s o r s w e r e r e c o r d e d on m a g n e t i c t ape .

I n s t r u m e n t a t i o n was not ava i l ab l e for weight flow d e t e r m i n a t i o n of the a u x i l i a r y b o u n d a r y - l a y e r b lowing s y s t e m ; h o w e v e r , a p p r o x i m a t e va lue s w e r e c a l c u l a t e d by a s s u m i n g choked flow at the ax ia l b l a d d e r o r i f i c e s and a n o m i n a l t e m p e r a t u r e of l l 0 ° F . A p r e s s u r e r e g u l a t o r was u s e d in s e t t i n g and m o n i t o r i n g a u x i l i a r y flow r a t e .

A m o r e c o m p l e t e d e s c r i p t i o n of the i n s t r u m e n t a t i o n m a y be found in Ref. 2.

3.3 PRECISION OF MEASUREMENTS

The u n c e r t a i n t i e s in s e t t i n g and m a i n t a i n i n g tunne l c o n d i t i o n s a r e as fo l lows :

Mach n u m b e r To ta l p r e s s u r e To ta l t e m p e r a t u r e Angle of a t t ack

:l:O. 005 +5 psf ±5°F ±0 .1 deg

The l ong i tud ina l v a r i a t i o n of Mach n u m b e r a long the t unne l c e n t e r - l i ne has a m a x i m u m va lue of +0 .02 .

AEDC.T R~69.98

The u n c e r t a i n t i e s a s s o c i a t e d with the t unne l p r e s s u r e m e a s u r i n g s y s t e m y i e l d u n c e r t a i n t i e s in the p r e s s u r e - c o e f f i c i e n t da ta as fo l lows:

M~ R e / f t x 10 -6 ACp

2 .2 0 .290 0 .0110 2 .2 1 .730 0 .0026 2 .5 0 .342 0 .0112 2 .5 2 .342 0 .0020

SECTION IV RESUL:rS AND DISCUSSION

Mach n u m b e r b o u n d a r y - l a y e r p r o f i l e s w e r e ob ta ined d u r i n g the a u x i l i a r y b o u n d a r y - l a y e r b lowing and a r e p r e s e n t e d in F ig s . 7 and 8. Data f r o m all t h r e e r a k e s wi th the l ong i tud ina l pos i t i on 0 .5 in. f o r w a r d of the aft edge of the s h e l l a r e p r e s e n t e d in Fig . 7. The a u x i l i a r y b o u n d a r y - l a y e r weight flow was v a r i e d f r o m 0 to 0 .30 l b / s e c . The bounda ry l a y e r a p p e a r e d to be t u r b u l e n t for <v > 0 .18 l b / s e c at Pt® = 325 psf and for ~v > 0 for Pt® = 400 psf. F i g u r e 8 is a c o m p a r i s o n of b o u n d a r y - l a y e r p r o f i l e s at v a r i o u s axia l pos i t i ons with and wi thout a u x i l i a r y b o u n d a r y - l a y e r b lowing. L a m i n a r flow e x i s t e d at al l m o d e l l o c a t i o n s for z e r o b lowing r a t e . A t u r b u l e n t b o u n d a r y l a y e r b e c o m e s n o t i c e a b l e at x / L _> 0 .55 for we igh t flow of 0 .30 l b / s e c . B o u n d a r y - l a y e r da ta ob t a ined us ing the p r e v i o u s l y e x i s t i n g b lowing s lo t w e r e i n d i c a t i v e of r e s u l t s r e - p o r t e d in Ref. 2 and a r e t h e r e f o r e not p r e s e n t e d .

A s u m m a r y of f lu t t e r cond i t i ons is p r e s e n t e d in Tab le I. At to ta l p r e s s u r e s of 350 and 988 psf, f l u t t e r was i nduced for the 0 . 0 0 2 0 - and 0. 0032- in . - t h i ck s h e l l s , r e s p e c t i v e l y , by r e d u c i n g the m o d e l cav i ty p r e s - s u r e at z e r o axia l load ing . On one 0. 0020- in . she l l , f l u t t e r condi t ions , . r e p o r t e d in Ref. 2, o f P t . = 300 to 510 psf, F = 13.0 to 25.9 , and APc =

0. 75 to 3. 6 w e r e dup l i ca t ed in an a t t empt to r e p e a t f lu t t e r . S e a r c h for f l u t t e r was u n s u c c e s s f u l b e t w e e n to ta l p r e s s u r e s of 300 to 400 psf . The s h e l l was a c c i d e n t l y buck led as Pt® was be ing i n c r e a s e d f r o m 400 psf . Cavi ty p r e s s u r e and APc w e r e z e r o at the t i m e of buckl ing .

REFERENCES

I. P e r k i n s , T. M. and B r i c e , T. R. "An I n v e s t i g a t i o n of the A e r o - e l a s t i c S tab i l i ty of Thin C y l i n d r i c a l She l l s at T r a n s o n i c Mach N u m b e r s . " A E D C - T R - 6 6 - 9 3 (AD632829), May 1966.

4

AEDC-TR-69.95

2. Br ice , T. R. " A e r o e l a s t i c Stabi l i ty Tes t s of Thin Cyl indr ica l Shells at Supersonic S p e e d s . " A E D C - T R - 6 8 - 7 9 (AD830407), Apr i l 1968.

3. Tes t Fac i l i t i e s Handbook (Seventh Edition). " P r o p u l s i o n Wind Tunnel Fac i l i ty , Vol. 5. " Arnold Eng inee r ing Development Cente r , Ju ly 1968.

4. P a r l i , C. L. and Sloan, E. H. " A e r o d y n a m i c Ca l ib ra t ion of the AEDC 16-Foot Supersonic Tunnel C o m p r e s s o r with F i b e r Glass F i r s t Cyl inder Rotor B l a d e s . " A E D C - T R - 6 9 - 7 9 , to be published.

5

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17

UNCLASSIFIED ~cu~t~ Classification

DOCUMENT CONTROL DATA-R & D ~eeuelty ¢laes|f icetion o! l i l le , ~ of abstracl end Indextn8 annofa t l~ must be en le~d when ~e o ~ e e l l t ~ o r t |e c laee l t l e~

t . O R I G I N A T I N G A C T I V I T Y (Co~o~le a u ~ o ~ |2a . R E P O R T S E C U R I T Y C L A S S I F I C A T I O N

Arno ld E n g i n e e r i n g Development C e n t e r J UNCLASSIFIED ARO, I n c . , O p e r a t i n g C o n t r a c t o r [2b. GRo~p Arno ld Ai r Force S t a t i o n , Tennessee N/A

3. R E P O R T T I T L E

AEROELASTIC STABILITY TESTS OF THIN CYLINDRICAL SHELLS AT SUPERSONIC SPEEDS (FOLLOW-ON TESTS)

4. O E S C R l P T I V E N O T E S ( ' ~ p e u f report and inclusive dates) J a n u a r y 7 t h r o u g h 20, 1969 - F i n a l Repor t

~. AU THORiS) CFirel name, middle init ial , last name)

Warren E. White, ARO, Inc.

S. R E P O R T D A T E 7a. T O T A L NO. OF' P A G E S 17b. NO. O F R i P S

April 1969 23 I 4 ~ . C O N T R A C T O R G R A N T N O .

F40600-69-C-0001 b. P R O J E C T N O . 9782

~.Program Element 61102F

d.

9a. O R I G I N A T O R ' S R E P O R T N U M B E R ( S I

AEDC-TR-69-98

gb. O T H E R R E P O R T NO(S) (Any O~ler numbers that may be eeei~lned th i s report)

N/A

' T h ~ s ' ~ ° ~ m e ~ ~ s ~ b j e c t t o /~ ' l~ i~ ia l e x p o ~ and each t r a n s m i t t a l l t o ~ r e ~ g n g ~ 4 e r n m ~ t s o r / f o r e i ~ a l s may be~mtade o ~ r i o ~

I . SCJ Id~SLEMENTARY N O T E S 12. S P O N S O R I N G M I L I T A R Y A C T I V I T Y

Available in DDC

Air Force O f f i c e of S c i e n t i f i c R e s e a r c h (SREM), A r l i n g t o n , V i r g i n i a 22209

iS . A B S T R A C T

Follow-on tests to an investigation to determine the dynamic char- acteristics of thin cylindrical shells were conducted in the Propulsion Wind Tunnel, Supersonic (16S). The model consisted of an ogive cylinder with the test shell located on the cylindrical portion of the model approximately 78 percent of the model length aft of the nose. Data were recorded at Mach numbers of 2.2 and 2.5 for 0-deg angle of attack and yaw. Flutter was induced on the 0.0020- and 0.0032-in.-thick shells by reducing the model cavity pressure. Boundary-layer measurements were also made at various boundary-layer blowing rate~.~

T~ docume~S~ subject ~cial exporf/contr~s and eac~-~ trans~, t.~l to yoreig5 kgover~ents o~forei~j~nationals'~~de\ only ~mtn I pri (SR l i n

DD ,'Tv"ssl 4 73

This document has been approved" for,.,/.G.~3_l_/l,. ~ p u b ~ c release,"t"~ -/~t,,_ , / d. tJ , -J- -1 L .

UNCLASSIFIED Security Classification

1 4 .

UNCLASSIFIED Security Classification

I

K E Y W O IRO II L. I N K A

R O L E V w T

dynamic characteristics

cylindrical shells

ogives

supersonic wind tunnels

flutter

boundary layer flow

missile models

/ /

- f

L I N K B l i . I N K C i

R O L E W T i R O L E W T

-..._

I I

J! y I ,

/ / Z J

AF~ 4rmld A/S T*~

I

UNCLASSIFIED Security Classification