Aerodynamic characteristics of forebody and nose strakes based on F-16 wind tunnel test experience. Volume 2: Data base

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N O T I C E THIS DOCUMENT HAS BEEN REPRODUCED FROM MICROFICHE. ALTHOUGH IT IS RECOGNIZED THAT CERTAIN PORTIONS ARE ILLEGIBLE, IT IS BEING RELEASED IN THE INTEREST OF MAKING AVAILABLE AS MUCH INFORMATION AS POSSIBLE

NASA Contractor Report 158922

(NBSA-CR-158922) kERODYNAMZC ~ 7 9 - 1 2 0 6 6 * CHARACTERISTICS OF FOREBODY AND NOSE STRAKES B A S E D O N F-16 WIND TUNNEL TEST EXPERIENCE.

VQLUME 2: D A T A BASE Final Report, 1 Sepu Unclas

1977 - 30 S e p . 1978 (General Dynamics/Fort 63/05 39019

AERODYNAMIC CHARACI'ERISTICS OF

FOREBODY AND NOSE STRAKES BASED

ON F-I 4 WIND TUNNEL TEST EXPERIENCE

VOLUME I1

DATA BASE

C.W. Smith I.C. Bhateley GENERAL DYNAMICS ,Cart Worth Division P. 0. B o x 748. Farr Worth, Texas 76101 Contract N-1-15006 September 1978 National Aeronautics artd Space Adrninistrariorr Lan~ley Resaarch Center Hsmpton, Virginia 23865 TABLE OF CONTENTS S e c t i o n Page

-- T i t l e -

LIST OF BIGURES i v INT RODUCT ION 1. L O W SPEED PITCH DATA 2 . LOW SPEED SIDESLIP DATA 3 , TRANSONIC PITCH DATA 4 , TRANSONIC SIDESLIP DATA i'RLCEDING PAGE &LANK IV.01' $J.4$;E:ED iii LIST OF FIGURES Figure T i t l e Page E f f e c t o f S l o t t e d Strake 222A, Configuration 9 40lF-5, K C 0 (a) L i f t and P i t c h i n g Moment (b) Drag Effect of S l o t t e d Strake Z22A, Configuration 401F-5, HT -10 (a) L i f t a n d Pitching Moment (b) Drag E f f e c t of S l o t t e d Strake 229A, Configuration 13 401F-16 (a) L i f t and Pitching Moment (b) Drag

E f f e c t of Rotating Strake7 Z34A ' and 233B,' Con- 15

f i g u r a t i o n 401F-16 ( a ) L i f t and F i t c h i n g Moment (b) Drag E f f e c t o f Rotating Strakes Z33A-Z33D, Configura- 17 t i o n 401F-16 (a) L i f t and Pitching Moment (b) Drag E f f e c t of Rotating S t r a k e s 233E-Z33H, Conf igura- 19 t i o n 401F-16 ( a ) L i f t and Pitching Moment (b) Drat2 E f f e c t of Rotating Strakes Z33C and 2331, Config- 21 u r a t i o n 401F-16 ( a ) L i f t and P i t c h i n g Moment (b) Drag E f f e c t o f Forebody Strakes 233 and 250, Configu- 23 r a t i o n 401F-16, U F fi 0 (a) L i f t and P i t c h i n g Moment (b) Drag E f f e c t of Forebody Strakes 233 and 2 5 0 , Configu- 25 r a t i o n 401F-16, LEF = 25O (a) L i f t and P i t c h i n g Moment (b) Drag iv &-15 EfXuzet: aE 1 1 ~ ~ 3 % ~ ~ 1 t 8 3 1 1 \ : 1 % : 1 lhE3,ect:L~xj \\ti.Qh S~;C&QG 31 2sD $363 :~nd Z66, P F 4 6 4% 9 0 , S Stxaksh, LEF (a) 1,kEt: m d f k & t ~ h i n ~ ; hblel\\ont (b) IJx~lp, (c) J:~~~rrzn\c$~?t:s kW = Q

( d l Xnruoslnnts, \?A' a 25"

l-L;t EZEaet: s f Ft'f@aLasi;l Stxotetr, Zh4 (SO, S Scmtchl) m e 1 43 $68 (44 ,5 S t a ~ ~ t b k ) , LEF 0 (3) I*$,Et: E~.II$ k ~ k i x ~ 'Eio\l\ar~% (b) Dcag LIST OF FIGURES (Continued) -re T i t l e Page 1-18 E f f e c t of Fuselage S t r e t c h , 264 (30.5 S t r e t c h ) 48

and 268 (44,5 S t s e t c h ) , U F 25'

( a ) L i f t and P i t c h i n g Moment Cb) Drag (c) Xncrements 1-19 E f f e c t of Leading Edge Flap Deflection w i t h

Strakes 267 and 270, YF -116 + 44.5 S t r e t c h

(a) L i f t and Pitching Moment ( b ) Drag 1-20 E f f e c t of Horizontal T a i l Deflection with

Strakes 267 and 270, YF-16 + 44.5 S t r e t c h

( a ) L i f t and P i t c h i n g Moment (b) Drag ( c ) Increments 1-21 E f f e c t of Nose, 276, and Canard, 286, YF-16, HT = 0 (a) E i f t and Pitching Moment (b) Drag (e) Increments 1 - 2 2 E f f e c t of Nose Strake 276, SF-16, HT = 25' (a) L i f t and P i t c h i n g Moment (b) Drag 1-23 E f f e c t of Forebody Strake Forward Extent (263, 6 1

264, Z72), YF-16 + 30.5 S t r e t c h , EFT 0

(a) E i f t and P i t c h i n g Moment (b) Drag (c) Increments 1-24 E f f e c t of Borebody Strake Fornard Extent (263, 64

264, 272), YF-16 + 30.5 S t r e t c h , HT 25'

( a ) L i f t and P i t c h i n g Moment ('ta) Drag (c) Increments

1-25 E f f e c t of Nose Strake 274, YF-16 + 30.5 S t r e t c h

( a ) L i f t and P i t c h i n g Moment (b) Drag LIST OF FIGURES (Continued) T i t l e - Page E f f e c t of Nose, 274, and Canard, 284, S t r a k e s , 69

YF-16 + 30.5 S t r e t c h , HT = 0

(a) L i f t and P i t c h i n g Moment (b) Drag E f f e c t of Canard S t r a k e 284, SF-16 3- 30.5 S t r e t c h , HT = 250 ( a ) L i f t and P i t c h i n g Moment (b) Drag E f f e c t of Forebody S t r a k e Shape (275, ZBQ, Z87), 73

YF-16 + 30.5 S t r e t c h , HT = 0

(a) L i f t and P i t c h i n g Moment (b) Drag (c) Increments E f f e c t of Forebody S t r a k e Shape (275, Z80, 287), 76 YF-16 4- 30.5 S t r e t c h , HT = 25" ( a ) L i f t and P i t c h i n g Moment (b) Drag ( c ) Increments 7 9

Effect of Forebody S t r a k e 287, YF-16 + 30.5

S t r e t c h (a) L i f t and P i t c h i n g Moment ( b ) Drag E f f e c t of Forebody S t r a k e Shape (288 and Z89), 81 HT = 0 YF-16 + 30.5 S t r e t c h , (a) L i f t and P i t c h i n g Moment (b) Drag E f f e c t of Forebody S t r a k e Forward Extent (263, 83

287, 2101, Z106), YF-16 + 30.5 S t r e t c h , HT = 0

(a) L i f t and Pitciling Moment (b) Drag (c) Increments E f f e c t of Forebody S t r a k e Forward Extent (263, 86

287, 2101, Z106), YF-16 + 30.5 S t r e t c h , HT = 25'

(a) L i f t and P i t c h i n g Moment (b) Drag (c ) Increments v i i LIST OF FIGURES (Continued) T i t l e YF-16 E f f e c t of Nose S t r a k e 2100, (a) L i f t and P i t c h i n g Moment (b) Drag E f f e c t : of H o r i z o n t a l T a i l D e f l e c t i o n w i t h 9 1 F-16 w i t h Wing W 3 B B Strake 2103, (a) L i f t and P i t c h i n g Moment (b) Drag Ef5ect o f Fcrebody S t r a k e S i z e (2103-2105)) F-16 93 critn Wing WZBB, HT = 0 (a) L i f t and P i t c h i n g Moment ( b ) Drag E f f e c t o f Forebody S t r a k e S i z e (2103-Z105), F-16 95 w i t h Wing W3BB, HT = 25O ( a ) L i f t and P i t c h i n g Moment (b) Drag E f f e c t of H o r i z o n t a l T a i l D e f l e c t i o n w i t h Strake 97 2103, F-16 w i t h Wing W24 ( a ) L i f t and P i t c h i n g Moment (b) Drag E f f e c t of Forebody S t r a k e S i z e (2103-2105), F-16 99 w i t h Wing W24, HT = 0 (a) L i f t and P i t c h i n g Moment ( b ) Drag E f f e c t o f Forebody S t r a k e S i z e (2103-2105), F-16 101 w i t h Wing W24, HT = 25P (a) L i f t and P i t c h i n g Moment (b) Drag E f f e c t of Forebody Strake Shape (2103, 2107-2109), 103 F-16 w i t h Wing W24 ( a ) L i f t and P i t c h i n g Moment (b) Drag E f f e c t o f Forebody Stsake Forward E x t e n t (2103, 105 F-16 w i t h Wing W24 2109) w i t h Nose Strske 2112, (a) L i f t and Pitching Moment (b) Drag v i i i LIST QF FIGURES (Continued) T i t l e Effect of Forebody Strake Shape (2103, 2107- Z109) with Nose Strake 2112, F-16 with Wing W 2 4 (a) Lift and Pitching Moment (b) Drag Effect of Nose Strake 2112 with Forebody Strake 2103, F-16 with Wing W24 (a) L i f t and Pitching Moment (b) Drag E f f e c t of Nose Strake 2112 wSth Farebody Strake 2109, F-16 with Wing W24 ( a ) L i f t and Pitching Moment (b) Drag E f f e c t of Canard Strake 279, F-16 (a) L i f t and Pitching Moment (b) Dreg E f f e c t of Nose Strake 2124 with Nose Probe, F-16 with Wing W 2 4 (a) L i f t and Pitching Moment (b) Drag E f f e c t o f Nose Strake 2124 without Nose Probe, F-16 w i t h Wing W 2 4 (a) LiEt and Pitching Moment (b) Drag E f f e c t of Nose Strake 2124, F-16, H T = 0 (a) L i f t and Pitching Moment (b) Drag Effect of Nose Strake 2124, P-16, I-fT = 25' (a) L i E t and Pitching Moment (b? Drag E f f e c t of Mose Strakes 2123-2127, F-16 (a) L i f t and Pitching Moment (b) Drag Effect a£ Nose Strake I n c l i n a t i o n (2124 and (2128 ) ,F-16 LX!$T OF FIGURES (Continued) T i t l e (a) tif t and P i t c h i n g Eio~uant (b:u Y J ~ ~ ? L $ 1-58 %f$ "lc ~9 Nose Straka Length (23.33, Z13W

urzc, Z2.L: W j , F-16

('fi) L x , & atz$ Pitctiing Momant: ( t ) Drsg E g f w t uf Nose Stsakes Z33J and 2332, F-16 1-54 (21) Lift and P i t c h i n g kbment

(BS Drag

1-55 Ff5ect o f N D S ~ Straka Z133, F-16 (a) L i f t and PLtchLng Efament: (bS 1-56 EfEoct oE Nose Shape, F-16 (a) LLEt ancI Pitching bi~ment (b) Brag and Z50, Con- Effect of Forebody Strakes 233 f iguratian SQlF-16 (s) Force and Nomants, -21" (b) Farce and bfomants, Q 1 3 1 ' EEfecc aE Fosebadg Strakes 263-266, YF-36 3- 2-2 3Q,5 S tratch

(a) Force and Fbmtlnts , a 1 2 6 '

(b) Xncmmancs, a 1l.26~ *,a ( c ) Force and bioments , Q -J+.

(d) lncxements , @ -320

(e) Force and EIomants , 0 . -36'

(El Increments, A 3Ga 2-3 EEEect oE Fosebody Strska Fanmrd Extanc (263,

264, E P 2 $ , PF-16 + 3 8 , s S t r e t c h

(a) Force and Efoments a =29' (h) Xncmrnetlts, a 127 d ( c ) Foxce and Mumants. q-33' ( d ) Increments, -33'

(el Force and biomants -37'

( E ) Xntlraments , Q -37 d

LIST OF FIGURES (Continued) Figure T i t l e

-

2-4 Effect of s t r a k e Size (263 and 266), YF-16 150 + 30.5 Stretch.

(a) Force and Moments, a' =26O (b) Force and Moments, C Y =32O ( c ) Force and Moments, a ~ 3 6 ' Effect of V e r t i c a l Tail with Forebody Strake 2 - 5 263, YF-16 3- 30.5 S t r e t c h (a) Force shd Moments, Q' ~ 2 6 ' (b) Force and Moments, a' -32" (c) Force and Moments, CZ -36' 2-6 Effect of V e r t i c a l Tail with Forebody Strake

266, YF-16 + 30.5 S t r e t c h

(a) Force and Moments , -26'

(b) Force and Moments, -32' ( c ) Force and Moments, 0 . -37' 2-7 E f f e c t of Forebody Strake Z67-Z70, YF-16 4- 159 30.5 S t r e t c h (a) Force and Moments u' m26 d (b) Increments, a =26 (c) Force and Moments, a -32' ( d ) Increments, & =3z0 (e) Force and Moments, a' -37' (f) Increments, 0 =37O 2-8 Effect of Forebody Strake Size (267 and 270), 165

YF-16 + 30.5 S t r e t c h

Q (a) Force and Moments, a =26 (b) Force and Moments, a ~ 3 2 ' (c) Force and Moments, a =37' 2-9 Effect of Fuselage S t r e t c h , 264 (30.5 S t r e t c h ) 168 and 268 (44.5 S t r e t c h ) (a) Force and Bfoments, a e26' (b) Force and Moments, a ~ 3 2 ~ ( c ) Force and Moments, a =36O 17 1 2-10 E f f e c t of Nose Strake 274, YF-16 -t 30.5 S t r e t c h (a) Force and Moments, a 10 (b) Force and Moments, a' 1 1 1 ' LIST O F FIGURES (Continued) T i t l e E f f e c t o f Nbse, 274, and Canard, 284, Strakes, 17 3

YF-16 + 30.5 S t r e t c h

(a) Force and Moments, a - 2 7 ' (b) Force and Moments, a -33' (c) Force and Moments, n -37' Effect o f Forebody Strake Shape (275, Z80, 257), YF-Y,6+30,5 S t s e t c h (a) Force and Momencs, a 127" (b) Force a n d Moments, a ~ 3 3 ' (c) Force and Moments, m37O Effect of Forebody Strske Size (263 and 2 8 9 1 ,

SF-16 + 30.5 S t r e t c h

(a) Force and Moments, -0 (b) Force and Moments a =Xl (c) Increments, 0 - 1 1 ' Effect of Nose, 276, and Canard, 286, Strakes, YF-16 (a) Force and >foments, a - 2 7 : (b) Force and Moments, 4 ~ 3 3 ~

( c ) Force and Moments , -37

Effect of Nose (277) and Canard (279,282) Strakes, YF-16 a -27' (a) Force and b f a m e n e s (b) Increments, a -27 c\ (c) Force and Moments, a =33* (d) Increments, a =330 (a) Force and M o m e n t s , a: -37 (E) Increments, 1137" Effect of Forebody Strake Foxward Extent (263, 287, 2101, 2106), YF-16 i 30,s S t r e t c h (a) Force and Moments, (r -26O (b) Increments, ~ 2 6 ~ Effect of Nose Str* 2100, PF-16 (a) Force and M o m e n t s , =21° (b) Force and Momants, a -26' (c) Force and Moments, a m 3 2 O ( d ) Farce and Moments, a -37' LIST OF FIGURES (Continued) T i t l e Page Effect of Forebody Stxake Size (2103-2105), 197 F-16 with Wing W3BB (a) Force and Moments,rrS llo (b) Forde and Moments ,a 21 ( c ) Force end Moments, CI = 26' Effect o f Forebody Strake Size (2103-2105), 200 F-I6 with Wing W24 Effect of Wing w i t h k r e b o d y Strake 2103, F-16 201 (a) Force and Moments, u -0 and lloo (b) Force and Moments,u=16 and 2 1 .

Effect of Leading Edge Flap Deflection with Forebody Strake 2103, F-16 with W i ~ g W3BB (a) Force and Moments, a 4 and 11 (b) Force and Moments, a 516 and 2 1 ' EffecZ of Forebady Strake Shape (2103, 2107- Z 1 0 9 ) , F-16 with Wing W24 (a) Force and Moments, a ~ 2 7 ' (b) Force and Moments, a -32' (c) Force and Moments, a '37: ( d ) Force and Moments, 4 2 Effect of Forebady Strake (2103 and 2109) Foma~xl Extent with Nose Strake 2112, F-16 with Wing W24 o (a) Force and Moments, a =26 (b) Force and Moments, a ~ 3 2 ' (c) Force and Moments, or =36: (d) Force and Moments, u 4 3 .

Effect of Nose Strakes 2110-2115, F-16 with Wing W24 (a) Force and Moments, a 626' (h) Xncrements, a =26* (c) Force and Moments, a ~ 3 2 ' (d) Increments, a =3z0 (e) Force and Moments, a =36 (f ) Increments, 01 =36O (g) Force and Moments, a 41' (h) Increments, a -41' LIST OF F I G m S ( Cont i.11ue d ) Page Fimre T i t l e

-

2-25 Effect of Nose Strakes Z l l O and 2117, F-16 222 &th Wing W24 (a) Force and Moments, a =26, (b) Force and Moments, '32, (c) Force and Noments, a =36 ( d ) 'r'orce and Moments, a +lo 2-26 E f f e c t o f Forebody Strakes 21.20 and 2121 with Canard Strake 279, F-16 30 and 32' (a) Force and Moments, a m27, 37 and 42' (b) Force znd Moments, a = 3 4 , 2-27 Effect of Nose Strake 2124, F-16 (a) Force and Moments, m = -11° Force and Moments, u = 0 ' ( b ) (c) Fsrce and Moments, a = 11' 2-28 Effect of Nose Strake 2124 with nose probe, F-16 w i t h Wing W 2 4

(a) Force and Moments , ct ~ 2 5 , 27 and 29'

36 and 40' (b) Fsrce and Moments, a -32, C 2-29 E f f e c t of Nose Stsake 2124 without nose probe, F-16 w i t h Wing W24 (a) Force and Moments, a ~ 2 5 , 27 and 3 0 : (b) Force and Moments, a ~ 3 2 , 36 and 40 2-30 Effect of Nose Strake I n ~ ~ l i n a t i o n z2124 and 2128), F-16 (a) Force and Moments, ~ 2 7 " (b) Increments, a ~ 2 7 ' (c) Force and Moments, -32'

(d) Inqremen ts , a ~ 3 2 ~

( e ) Force and Moment;, a =37 (f) Increments, a =37 (g) Force and Moments, a 4 2 '

(h) Incraments , 142'

2-31 Effect a f Nose Strakes 2123-2127, F-i6 (a) Force and Moment:, CY =27* (b) Increments, a -27 (c) Force and Moments, ck -3e0 ( d ) Increments, (Y =30° (e) Force and Moments, a -32* xiv LIST OF FIGURES (Continued) Figure . T i t l e

-

( f ) In,cremer.ts , a =32O

(g) Force and Moments a =37 (h) Increments, a=37 0' (i) Force and Moments a 4 2 ' ( 5 ) Increments, ff ~42' 2-32 Effect of Nose Strake Length (2131, Z13kQ, 2131B) F-16 (a) Force and Moments, '26'

(b) Increments , a -26'

(d) bcrements , a -32'

(e > Ft+. rip a n d Moments, a -38'

(f) T i ? e n s , a = 37

(g) Fo.ise and Moments, a (h) Increments , a =3g0 2-33 Effect of Nose Strakes 2131 and 2132, F-16

(a) Force and Moments , a -26O

(b) Force and Moments, ff - 3 2 ' (c) Force and Moments, a-37' ( d ) Force and Moments, ff 139' 2-34 Effect of Nose Strake 2133, F-16

(a) Force and Moments , a 1 2 6 '

( b ) Force and Moments, a -30' ( c ) Force and Moments, a 1 3 7 ' (d) Force and Moments, Cu =3g0 2-35 E f f e c t of Nose Shape, F-18 (a) Force and Moments, a -26' (b) Force and Moments, a -32O (c) Force and Moments, -37, (d) Force and Moments, a -39 2-36 Effect of Nose Strake 2131 with Nose N7 and V e r t i c a l T a i l O f f , F-16

(a) Force and Moments, a - 26'

(b) Force and Moments, a = 32: (c) Force and Moments, ff = 37

Xd) Force and Moments, - 3'9'

3-1 Effect of Canard St r a k e Z 1 , Conf i g u r a t ion

401F-2 w i t h Twin V e r t i c a l T a i l s , M - 0.80

ORIGINAL PAGE J S OF POOR. QUALITY LIST OF FXGUMES (Contimad) 9-4 EEf a c t sE Gatxt\~:d S k x a k ~ Z'Scri, C ~ n f tguxat$dl~

4058-5, IaS 25') M - 0.80

( : ( I LLEt x ~ i d ,P;tkch&n$ b\im111~nt Cb) Q x " ~ ~ L ~ x ~ Q ScnLa ( c ) bgng, Srnnl3, ScsLi3.

$45 EEEonb 83 Can.nml Sexaka ZZA, C~xzE:LgusacEon

48LP-2 w;tCh ' k \ v i r ~ Saxt;&c:rl, TaiJ,s, M Q 68

(a) ~tl,iZ t and Pi,.i=clxLng EXox11o'1;1t (b) Dza8, L ~ r g e Scs3n (c) Drug, Sn1n2,X ScnLa LIST O F FIGURES (Continued) Figure T i t l e Page 3-8 Effect of Canard Strake 2 2 , Configuration 2 99 401F-2 with Twin V e r t i c a l Tails (a) L i f t and Pitching Moment (b) Drag, Large Scale (c) Drag, Small Scale Effect of Canard Strake 2 3 , Configuration 40lF-4, M = 0.80 (a) L i f t and Pitching Moment a (b) Drag, Large Scale (c) Drag, Small Scele Effect of Canard Strake 23, Configuration

401P-4, M - 0.90

(a) L i f t and Pitching Moment (b) Drag, Large Scale (c) Drag, Small Scale Effect of Canard Strake 2 3 , Configuration 401F-4, M = 1.20 (a) L i f t and Pitching Moment (b) Drag, Large Scale (c) Drag, Small Scale Comparison of Canard Strskes ( Z l A , Z l B , 23), ConfFguration 401F-5, M = 0.80 (a) L i f t and Pitching Moment (b) Drag, Large Scale ( c ) Drag, Small Scale Comparison of Canard Strakes (ZIA, ZlB, 23), Configuration 401F-5, M = 1.20 (a) L i f t and Pitching M~ment (b) Drag, Large Scale (c) Drag, Small Scale Effect of Leading Edge Flap Deflection with Forebady Strake 24, Configuration 401F-5, M = 0.80 ( a ) L i f t and Pitching Moment (b) Drag, Large Scale (c) Drag, Small Scale LIST OF FIGURES (Continued) F i g u r e Page 3-15 E f f e c t o f Leading Edge F l a p D e f l e c t i o n w i t h o u t 320 a S t r a k e , C o n f i g u r a t i o n 401F-5, M = 0 , 8 0 (a) L i f t and P i t c h i n g Moment (b) Drag, Large S c a l e ( c ) Drag, S m a l l S c a l e Effect o f Forebogy S t r a k e 24, c o n f i g u r a t i o n 323 40lF-5, LEF = 15 , M = 0.80 (a) L i f t and P i t c h i n g Moment (b) Drag, Large S c a l e (c) Drag, %mall S c a l e Effect o f Farebogy S t r a k e 24, C o n f i g u r a t i o n

40lF-5, LEI? - 25 , M = 0.80

(a) L i f t and P i t c h i n g Moment (b) Drag, Large S c a l e ( c ) Drag, Small Scale Effect o f Fssebody - S t r a k e Blending ( 2 4 ) , Configuratior; 401F-5, LEF 0 , M 0.80 (a) L i f t and P i t c h i n g Moment (b) Drag, Large S c a l e (c) Drag, Small S c a l e

Effect of Forebody - S t r a k e Blending ( 2 4 ) , 332

C o n f i g u r a t i o n 401F-5, M = 1 . 2 0 (a) Lift and Pitching, Moment (b) Drag,, Large S c a l e (c) Drag, Sm,all Scale E f f e c t of Forebody S t r a k e Blending ( 2 4 ) ,

Configuration 4013'-5, LEF - 10'. M = 0.80

(a) L i f t and P i t c h i n g Moment (b) Drag, Large S c a l e (c) Drag, S m a l l S c a l e E f f e c t of Forebody S t r a k e 24 and 2 5 , Con- f i g u r a t i o n 401F-5, LEF = 0, M = 0.80 (a) L i f t a n d P i t c h i n g Moment (b) Drag, L a r g e Scale (c) Drag, Small S c a l e ( d ) Increments LIST OF FIGURES (Continued) Figure Title Page 3-22 Effect of Forebody Strakes 24 and'Z5, Con- 342 figuration 401F-5, M = 1.20 (a) Lift and Pitching 24oment (b) Drag, Large Scale (c) Drag, Small Scale (d) Increments 3-23 Effect of Forebody Strakes g4 and Z 5 , Con- 346 figuration 401F-5, LEF = 10 , M = 0.80 (a) Lift and Pitching Moment (b) Drag, Large Scale (c) Drag, Small Scale (d) Increments 3-24 Effect of Delta Planfonn Forebody Strakes, 3 50 (27-ZlO), Configuration 785, LEF = 0, M = 0.80 (a) Lift and Pitching Moment (b) Drag, Large Scale (c) Drag, S-11 Scale (d) Increments 3-25 Effect of Delta Planform Forebody Strakes 3 54 . (27-210) Configuration 785, M = 1.20 (a) Lift and Pitching Moment ( b ) Drag, Large Scale (c) Drag, Small Scale (d) Increments 3-26 Effect of Delta Flanform Forebody Shrakes 358 (27,210) Configuration 785, LEF = 5 , M = 0.80 ( a ) L i f t and Pitching Moment (b) Drag, Large Scale (c) Drag, Small Scale (d) Increments 3-27 Effect of Delta Planform Forebody Strgkes 362 (27, Z10) , Configuration 785, LEF = 15 , M = 0.80 (a) Lift and Pitching Moment (b) Drag, Large Scale (c) Drag, Small Scale (d) Increments x i x LIST OF FIGURES (Continued) Figure Title Page

-

3-28 Effect of Horizontal Tail Deflection with 366 Forebody Strake 27, Configuration 785, M = 0.80 (a) Lift and Pitching Monent (b) Drag, Large Scale (c) Drag, Small Scale 3-29 Effect of Horizontal Tail Deflection without 369 a Strake, Configuration 785, M = 0.80 (a) Lift and Pitching Moment (b) Drag, Large Scale (c) Drag, Small Scale 3-30 Effect of Strake 27 on Horizontal Tail Effec- 372 tiveness, Configuration 785, M = 0.80 (a) Lifc and Pitching Moment (b) Drag, Large Scale (c) Drag, Small Scale ( d ) Increments 3-31 Effect of Leading Edge Flap Deflection with 37 6 Strake 27, Configuration 785, M = 0.80 (a) Lift and Pitching Moment (b) Drag, Large Scale (c) Drag, Small Scale 3-32 Effect of Forebody Strake 27, Configuration 379 786, LEF = 0, M = 8.80 (a) Lift and Pitching Moment (b) Drag, Large Scale ( c ) Drag, Small Scale (d) Increments 3-33 Effect 05 Forebody Strake 27, Configuration 383 766, M = 1.20 ( a ) Lift and Pitching Moment (b) Drag, Large Scale (c) Drag, Small Scale LIST OF FIGURES (Continued) Figure Title Page

-

3-34 Effect of Fosebody Strake 27, Configuration 386 786, LEF = 5 , M = 0.80 (a) Lift and Pitching Moment (b) Drag, Large Scale (c) Drag, Small Scale 3-35 Effect of Ogee Planform Forebody Strakes (214, 38 9 216-Z18), Configuration 40lF-5, M = 0.80 (a) Lift and Pitching Moment (b) Drag, Large Scale (c) Drag, Small Scale ( d ) Increments 3-36 Effect of Forebody Chines (220, 221) and 39" Canard Strake ZlA, Configuration 401F-lOA, LEF = 0 , M = 0.80 (a) Lift and Pitching Moment (b) Drag, Large Scale ( c ) Drag, Small Scale 3-37 Effect of Forebodg Chines (220,, 221) and 396 Canard Strake ZIA, Configuration 401F-1OA, M = 1.20 (a) Lift and Pitching Moment (b) Drag, Large Scale (c) Drag, Small Scale

3 - 38 Effect of Forebody Chines (220, 221) and 394

Canard Skrake ZlA, Configuration 401F-10A,

LEF - 10, M = 0.80

(a) Lift and Pitching Moment (b) Drag, Large Scale (c) Drag, Small Scale 3-39 Effect of Forebody Chines (228, 221). Con- 402 figuration 401F-10A, LEF = 25 , M = 0.80 (a) Lift and Pitching Moment (b) Drag, Large Scale (c) Drag, Small Scale xxi LIST OF FIGURES (Continued) T i t l e

- , PaRe

3-40 Comparison o f Forebody S t r a k e . 222 with Canard 405

S t r a k e ZlA, c o n f i g u r a t i o n 401F-5, LEF = 0, M - 0.80

(a) L i f t and P i t c h i n g Moment (b) Drag, Large S c a l e (c) Drag, Sx: .,I S c a l e 3-41 Comparison o f Forebody S t r a k e s 222 and 223 408 w i t h Canard Strake Z U , C o n f i g u r a t i o n 401F-5, LEF -10, M = 0.80 ( a ) L i f t and P i t c h i n g Moment (b) Drag, Large S c a l e (c) Drag, Small S c a l e 3-42 Effect of Forebody S t r a k e Shape (224-Z27), C o n f i g u r a t i o n 401F-10A, LEF = 0 , M = 0.80 ( a ) L i f t and P i t c h i n g Moment (b) Drag, Large S c a l e (c) Erag, Small Scale (d) Increments 3-43 E f f e c t of Forebody S t r a k e Shape ( 2 2 4 - 2 2 6 ) , C o n f i g u r a t i o n 401F-10A, LEF = 0 , M = 0.9Q ( a ) L i f t and P i t c h i n g Moment (b) Drag, L a r g e S c a l e ( c ) Drag, Small S c a l e , (d) Increnents 3-44 E f f e c t of Forebody S t r a k e Shape 6224-227), C o n f i g u r a t i o n 401F-10A, LEF = 1 0 , M = 0 . 3 0 (a) L i f t and P i t c h i n g Moment (b) Drag, Large S c a l e (c) h a g , Small S c a l e (d) Increments 3-45 Effect o f Forebody S t r a k e Shape (224-226))

C o n f i g u r a t i o n 401F-1OA, LEF = l o 0 , M = 0.90

(a) L i f t and P i t c h i n g Moment (b) Drag, Large Scale ( c ) Drag, S m a l l Scale (d) Increments LIST OF FIGURES (Continued) Figure Title Page 3-46 Effect of Forebody Strake Shape 6224-~27), 4 27 Configuration 401F-10A, LEF = 25 , M = 0.80 (a) Lift and Pitching Moment (b) Drag, Large Scale (c) Drag, Small Scale (d) Increments 3-47 Effect of Forebody Strake Shape (228-231), 433.

Configuration 401F-16, LEF = 0, M = 0.80 (a) Lift and Pitching Moment (b) Drag, Large Scale (c) Drag, Small Scale (d) Increments 3-48 Effect of Forebody Strake Shapeo(Z28-Z31), 435 Configuration 4013'-16, LEF = 10 , M = 0.80 (a) Lift and Pitching Moment (b) Drag, Large Scale (c) Drag, Small Scale (d) Increments 3-49 Effect of Forebody Strake Shapeo (Z28-231) , 439 Configuration 401F-16, LEF = 25 , M = 0.80 (a) Lift and Pitching Moment (b) Drag, Large Scale ( c ) Drag, Small Scale (d) Increments 3-50 Effect of Forebody Strakes 229 gnd 232, 44 3 Configuration 401F-16, LEF = 10 , M = 0.8U (a) Lift and Pitching Moment (b) Drag, Large Scale (c) Drag, Small Scale 3-51. Effect of Forebody Strakes 229 gnd 232, 446 Configuration 401F-16, LEF = 25 , M = 0.80 (a) Lift and Pitching Moment (b) Drag, Large Scale (c) Drag, Small Scale (d) Increments LIST OF FIGURES (Continued) Figure T i t l e 3-52 Effect of Forebody S t s a k e s 231 and 2 3 3 , C o n f i g u r a t i o n 401F-16, LEF = 0, M = 0 . 8 0 (a) L i f t and P i t c h i n g Moment (b) Drag, Large S c a l e (c) Drag, Small S c a l e (d) Increments 3-53 E f f e c t o f Forebody S t r a k e s 231 and 233, 4 54 C o n f i g u r a t i o n 401F-16, LEF = 1 0 ' . M = 0.80 (a) ~ i f t and P i t c h i n g Moment

(9 Drag, Large S c a l e

C o n f i g u r a t i o n 40lF-16, LEF = 25 , M = 0.80

(a) L i f t and P i t c h i n g Moment (b) Drag, L a r g e S c a l e (c) Drag, Small Scale (d) Increments 3-55 Effect of Forebody S t r a k e s 233 and 250, Configuration 40lF-16E, M = 0 . 6 0 (a) L i f t and P i t c h i n g Moment (b) Drag, Large S c a l e ( c ) h a g , Snall S c a l e 3-56 E f f e c t of Forebody Strakes 233 and Z50, 465 C o n f i g u r a t i o n 40lF-16E, LEF = 0 , M = 0 . 8 0 ( a ) Lift and P i t c h i n g Moment (b) Drag, Large S c a l e (c) Drag, S m a l l Scale 3-57 E f f e c t of Forebody S t s a k e s 233 and Z50, C o n f i g u r a t i o n 401F-16E, M = 9.90 (a) L i f t and P i t c h i n g Moment (b) Drag, Large S c a l e (c) Drag, Small S c a l e LXST O F FIGURES (Continued) T i t l e Page.

E f f e c t sf Forebodp S t r a k e s Z33 and 250, C o n f i g u r a t i o n 401F-16E, M = 1 . 2 0 (a) L i f t and P i t c h i n g Noment (b) Drag, Large S c a l e (c) Drag, Small S c a l e ~ k f e c t of Forebodg S t r a k e s 233 agd ZSO, 474

Gonfiguration 4OlF-ICE, LEF = 25 , >I = 0 . 8 0

( a ) Lift: and P i t c h i n g Ploruent (b) Drag, L a r g e S c a l e (c) Drag, Small S c a l e E E E e c t o f Forebodp Stxake Shape (233, 477

248-250), C o n f i g u r a t i o n 401F-16E, P I - 0.90

(a) Lift and P i t c h i n g Moment (b) Drag, Large S c a l e (c) Drag, Small S c a l e Effect of Forebody S t r a k e Shape (263-266, 480 271$, YF-16 4- 30.5 S t r e t c h , M = 0.80 (a) Llf t and P i t c h i n g Pioment (b) Drag, Large S c a l e (c) Drag, Small S c a l e (d) I n c r m e n t s E f f e c t o f Forebody S t r a k c Shape (263-266, 484

271, SF-16 + 30.5 S t r e t c h , LEF = 0, PIm 0.90

(a) Lift arid P i t c h i n g hf~ment (b) Drag, U r g e S c a l e (c) Drag, Small S c a l e (d) Increments E f f e c t o f Forebody S t r a k e Shape (263-266, 488 Z 7 l . ) , YF-16 .t 30.5 S t r e t c h , 11 = 1 . 2 0 (a) Lift and P i t c h i n g hZoment (b) Drag, Large S c a l e ( c ) Drag, Small Scale (d) lncsemen t s LIST OF FIGUBES (Continued) Figure T i t l e Page 3-64 E f f e c t o f Forebody S t r a k e Shape (263-266, 492

271)) YF-16 + 3 0 . 5 S k e t c h , LEF = 25 , M = 0.90

( a ) L i f t and P i t c h i n g Moment (b) Drag, Large S c a l e (c) Drag, Small S c a l e Effect of Forebody S t r a k e Shape (263, 264,. ' 495

287, 288) YF-16 + 30.5 S t r e t c h , M = 1 . 6 0

( a ) L i f t and P i t c h i n g Moment (b) Drag, Large Scale (c) Drag, Small S c a l e E f f e c t of Forebody S t r a k e Shape (263, 2 6 4 , 498

287, 288) YF-16 + 30.5 S t r e t c h , M = 2 . 0 0

(a) Lift and P i t c h i n g Moment (b) Drag, L a r g e S c a l e (c) Drag, Small S c a l e

E f f e c t o f Nose S t r a k e s 273 and 274, YF-16 + 501

30.5 S t r e t c h , M = 0 . 8 0 (a) L i f t and P i t c h i n g Moment (b) Drag, L a r g e S c a l e ( c ) Drag, S m a l l S c a l e

E f f e c t of Nose S t r a k e s 273 and 274, YF-16 +

3 0 . 5 S t r e t c h , M - 9 . 9 0

(a) L i f t and P i t c h i n g Moment (b) Drag, L a r g e S c a l e (c) Drag, Small S c a l e

E f f e c t o f Nose S t r a k e s 273 and 2 7 4 , YF-16 + 507

30.5 Strezch, M = 1 . 2 Q (a) L i f t and P i t c h i n g Moment (b) Drag, Large S c a l e (c) Drag, Small S c a l e Effect o f Forebody S t r a k e Size (272, 275,

2 8 0 ) , YF-16 + 30.5 S t r e t c h , M = 0 . 8 0

( a ) L i f t and P i t c h i n g Moment ( b j Drag, Large S c a l e ( c ) Drag, S m a l l S c a l e ( d ) I n c r e m e n t s LIST OF FIGURES (Continued] T i t l e Page 3-71 Effect of Forebody Strblce Size (272, 275, Z80) 5 14 YF-16 -t 30.5 S t r e t c h , LEF = 0, M = 6,90 (a) Lift and YEtching Moment (bj Drag, Large Scale (c) Drag, Small Scale (d) Increments 3 9.7 2 Effect of Fosebody Strake Size f Z 7 2 , 275, 280) 5 18

YF-16 + 38.5 S t r e t c h , M = 1 . 2 0

(a) L i f t and Pitehing hIBment (b) Drag, Large Scale (c) Drag, Small Scale (d) Increments 3-73 Effect of Forebody Srrake Sizeo(Z72, 275, Z80) 522

YF-16 + 30.5 S t r e t c h , LEF = 25 , M e 0.90

(2) L i f t s n d Pitching Moment (b) Drag, Large Scale (c) Drag, Small Scale (d) Increments

3-74 E f f e c t of Canard Strakes Z 1 D and 281, YF-16 + 526

3 0 . 5 S t r e t c h , E i = 0 . 8 0 (a) L i f t and Pitching Moment (b) Drag, Large Scale (c) h a g , Small Scale

3-75 Effect of Canard Strakes Z 1 D and ZS1, YF-16 + 529

3 0 . 5 S t r e t c h , PI = 0 . 9 0 (a) L i f t and Pitching Moment (b) Drag, Large Scale (c) Drag, Small Scale

3-76 Effect of Canard Strakes Z 1 D and 281, YF-16 + 532

30.5 S t r e t c h , M = 1 . 2 0 (a) L i f t and Pitching Moment (b) Drag, Large Scale (c) Drag, Small Scale LIST OF FIGURES (Continued) T i t l e F i g u r e P 3-77 Effect of Canard S t r a k g s ZlD and Z81, 9'-16 f 30.5 S t r e t c h , L,EF = 25 , M = 0.90 ( a ) L i f t and P i t c h i n g Moment (b) Drag, Large S c a l e ( c ) Drsg, Small S c a l e E f f e c t of Nose S t r a k e 2100, F-16, M = 0.90 ( a ) L i f t and P i t c h i n g Moment (b) Drag, Large S c a l e ( c ) Drag, Small S c a l e E f f e c t of Forebody S t r a k e Shape (2103, Z108), F-16, M = 0 . 9 0 (a) Lift and P i t c h i n g Moment (b) Drag, L a r g e S c a l e (c) Drag, Small Scale Effect of Forebsdy Strake Shape ((2103, Z108), F-16, M = 1 . 2 0 (a) L i f t and P i t c h i n g Moment (b) Drag, Large S c a l e (r) Drag, Small S c a l e 54 7 E f f e c t of Forebody S t r a k e Forward E x t e n t (2103, 2109) , F-16, M = 0.90 (a) L i f t and P i t c h i n g Moment (b) Drag, L a r g e S c a l e ( c ) h a g , Small Scale (d) Increments Effect of Forebody S t r a k e Forward E x t e n t (2103, 551

Z109), F-16, M - 1 . 2 0

(a) i i f t and P i t c h i ~ g Moment (b) Drag, Large S c a l e ( c ) Drag, Small S c a l e ( d ) Increments E f f e c t of Canard S t r a k e 21, C o n f i g u r a t i o n 401F-2 w i t h Twin V e r t i c a l TaiAs, M = 0 . 8 0 (a) F o r c e and Momexits, a = f 6 (b) F o r c e and Moments, u = 27' LIST OF FIGURES (Continued) Figure Title Page 4-2 Effect of Canarg Strake Z l A , Configuration 401F-2 with 7.5 Twin Vertical Tails, M = 0.80 Effect of Canarg Strake ZlA, Configuration 481F-a with 7.5 Twin Vertical Tails, M = 1.20 Effect of Canagd Strake ZlA, Configuration 401F-2 with 15 Twin Verticah Tails, M = 1.20 ( a ) Force and Moments, a = 0 ( b ) Force and Moments, a = 1 5 ' (c) Force and Moments, a = 20° Effect of Canasd Strake ZlA, Configuration 401F-2 w&th 15 Twin Vertical Tails, LEF = 25 , M = 0.80 (a) Force and Moments, a = 1 5 ' (b) Force and Moments, a = 21° (c) Force and Moments, a = 2 4 ' Effect of Canard Strake ZlA, Configurationo 401F-2 with Single Vertical Tail, LEF = 25 , M = 0.80 (a) Force and Moments, a = 1 5 ' (b) Force and Moments, o = 2 1 ' (c) Force and Moments, a = 2 4 ' Effect of Canatdostrake ZlA, Configuration 401F-5, LEF 25 , M = 0.80 (a) Force and Moments, a = 1 5 ' Q (b) Force and Koments, a =

(c) Force and Moments, = : g o

Effect of Forward Vertical Tail Movement with Canard Strake Zlb, Configuration 401F-5, M = 1.20 (a) Force and Moments, a = 1 0 ' (b) Force and Moments, a = 1 5 ' Effect of Forward V e a L : . c a l Tail Movement with Canard Sgrake Z l A , Configuration 401F-5, LEF = 10 , M = 0.80 (a) Force and Moments, a = (b) Force and Moments, o = : ! o

*

Y r r P - 0 0 0 0 Y Y Y 3 o n n m I D I D c ' ' ' D D P B P S % a a a t C

z z z-

Q U O

I l e m Z

= f s g lb rt rt rt V l t n V 1 Q M P P e(Gm o a o LIST OF FIGURES (Continued) Figure Title 4- 18 Effect of Forebody Strakes 24 and 25, Config- 594 uration 401F-5, M = 1.20 (a) Force and Moments, a = 1 0 ' (b) Increments, a = 1 0 ' = 1 5 ' (c) Force and Moments, (d) Increments, a = 15 4-19 Effect of Forebody Strakgs 24 and Z5, Config- 598 uration 401F-5, LEF = 10 , M = 0.80 (a) Force and Moments, a = 1 5 ' (b) Increments, a = 1 5 ' (c) Force and Moments, o = 2 0 ' (d) Increments, a = 2 0 ' (e) Force and Moments, a = 2 5 ' (f) Increments, a = 2 5 ' 4-20 Effect of Forebogy Strake 24, Configuration 604 401F-5, LEF = 15 , M = 0.80 (a) Force and Moments, a = 2 0 ' ( b ) Force and Moments, = 2 5 ' 4-21 Effect of Forebody Strake 24 on Vertical 606 Tail Effectiveness, Configuration 40l.F-5, M = 0.80 (a) Force and Moments, a = 2 0 ' (b) Strake-off Increments, a = 2 0 ' (c) Strake-on Increments, or = 2 0 ' (d) Force and Moments, a = 2 5 ' ( e ) Strake off Increments, a = 2 5 ' (f) Strake on Increments, a = 2 5 ' 4-22 Effect of Forebody Strake 25, Configuration 6 12 401F-4, M = 0,80 (a) Force and Moments, a = 1 6 ' (b) Force and Moments, a = 2 0 ' (c) Increments, a = 2 0 ' (d) Force and Moments, & = 2 5 ' (e) Increments, a = 2 5 ' xxxi LIST OF FIGURES (Continued) T i t l e Page 4- 23 Effect of Forebody Strake Z 5 , Configuration 6 17

. 401F-4, M = 1 . 2 0

(a) Force and Moments, a = 1 1 ' (b) Increments, a = 1 1 ' (c) Force and Moments, oa = 1 5 ' (d) Increments, a = 15 4-24 Effect of Delta Pbanform Forebody Strakes 621 (27-ZlO), Configuration 785, f;EF = 0, M = 0.80 (a) Force and Moments, a = 14 (b) Increments, a = 1 4 ' (c) Force and Moments, oa = 20' (d) Increments, a = 2 0 ( e ) Force and Moments, = 2 4 ' (f). Increments, a = 24 4-25 Effect of Delta Planfarm Forebedy Strakes (27-210) , Configuration 785. = 1.20 (a) Force and Moments, oo = 12 (b) Increments, a = 1 2 ( c ) Force and Moments ,oo = 1 7 ' (d) Increments, a = 17 Effect of Delta Planform Forebody Stgakes 4-26 (27,210) , Configuration 785, LXF = 5 , M = 0.80 ( a ) Force and Moments, a = 14' (b) Force and Moments, oa = 2 0 ' (c) Increments, a = 20 ( d ) Force and Moments, oa = 2 4 '

(e) Increments, - 2.4

4-27 Effect of Delta Planform Forebody Strgkes (27,210), Configurati~n 7 8 5 , LEF = 10 , M = 0 . 8 0 (a) Force and Moments , oa = 1 4 ' (b) Increments, a = 14 (c) Force and Moments, ' a = 2 0 ' ( d ) Increments, a = 20 (e) Forcie and Moments, o = 24'

(f) Increments, a - 24'

LIST OF FIGURES (Continued) Page F > + U L - e Title

-

\ 4- 28 Effect of Delta Planform Forebody Strgkes 64 2 (27, 210) Configuration 755, LEF = 15 , M = 0.80 (a) Force and Moments, a = 1 4 ' (b) Increments, 0 = 1 4 ' (c) Force and Moments, ff = 1 9 ' (d) Increments, a = 19 ( e ) Force and Moments. o : = 2 4 ' (f) Increments, a = 2 4 ' 4-29 Effect of Forebody Strake 27, Configuration 648 786, M = 1.20 4-30 Effect of Fogebody Strake 27, Configuration 64 9 786, LEF = 5 , M = 0.80 (a) Force and Moments, a = 2 0 ' (b) Increments, o : = 20' (c) Force and Moments, oa = 2 5 ' (d) Increments, CY Is 25 4-31 Effect of Forgbody Strake 27, Configuration 786, LEF = 10 , M = 0.80 (a) Force and Moments, a = 2 0 ' (b) Increments, a = 2 0 ' (c) Force and Moments a = 2 5 ' (d) Increments, a = 25 4 - 3 2 Effect of Forgbody Strake 27, Configuration 786, LEF = 15 , M = .0.80 (a) Force and Moments , o a = 2 0 ' (b) Increments, a = 20 ( c ) Force and Moments, a = 2 5 ' ( d ) Increments, a = 25 4-33 Effect of Ogee Planform Forebody Strakes (214, Z16, 218)) Con3iguration 401F-5, M = Q.80 (a) Force and Moments, a ! = 2 0 ' (b) Increments, = 2 0 ' (c) Force and Moments, off = 2 5 ' ( d ) Increments, a = 25 xxxiii LIST OF FIGURES (Continued) Figure Title Page 4-34 Effect of Forebody Chines (220, 221) and Canard Spake ZIA, Configuration 401F-10k, LEF = 10 ,' M = 0.80 (a) Force and Moments, a = 2 0 ' (b) Force and Moments , a = 2 5 ' Effect of Forebodyochine 220. Configuration 401F-10A, LEF = 25 , M = 0.80 (a) Force and Moments, a = 2 0 ' (b) Force and Moments, a = 2 5 ' Effect of Forebody Strake Shape 6224-227), Configuration 401.F-10A, LEF =010 , M = 0.80 (a) Force and Moments, a = 2 0 (b) Increments, a = 2 0 ' (c) Force and Moments, = 2 5 ' (d) Increments, a = 25 (224-226), Effect of Forebody Strake Shape Configuration 40lF-lOA, M = 0.90 (a) Force and Moments, = 2 0 ' (b) Increments, a = 20 (c) Force and Moments, oa = 2 5 ' (d) Increments, a = 25 Effect of Forebody Strake Shape 6224-227).

Configuration 401F-10A, LEF =025 , M = 0.80 (a) Force and Moments, on = 20 (b) Increments, a = 20 (c) Force and Moments, oa = 2 5 ' (d) Increments, CY = 25 Effect of Forebody Strake Shapeo (228-231) , Configuration 401F-16, LEF = 10 , M = 0.80 (a) Force and Moments, a = 2 0 ' (b) Force and Moments, oa = 2 5 ' (c) Increments, a = 25 Effect of Forebody Strake Shapeo(Z28-Z31), Configuration 401F-16, LEF = 25 , M = 0.80 ,o (a) Force and Moments, oa = 20 (b) Increments, a = 20 (c) Force and Moments, a = 2 5 ' (d) Increments, a = 25 LIST OF FIGURES (Continued) Title Page Figure 4-41 Effect of Forebody Strakes 289 and 232, Con- 688 figuration 401F-16, LEF = 10 M = 0.80 (a) Force and Moments, a = 20 (b) Force and Moments, a = 2 5 ' 4-42 Effect of Forebody Strakes Z89 and 232, Con- 690

figuration 401F-16, LEF - 25 M = 0.80

(a) Force and Moments, a = 20 (b) Force and Moments, a = 2 5 ' 4-43 Effect o f Forebody Strakes Z a l and 233, Con- 692 figuration 401F-16, LEF = 10 M = 0.80 (a) Force and Moments ,oa = 20 (b) Increments, a = 20 (c) Force and Moments ,oa = 2 5 ' (d) Tncrements , at = 25 4-44 Effect of Forebody Strakes Z a l and 2 3 3 , Con- 696 figuration 401F-16, LEF = 25 M = 0.80 (a) Force and Moments, a = 20 (b) Increments, a = 2 0 ' (c) Force and Moments, a = 25' (d) Increments, n -- 2 5 ' 4-45 Effect of Forebody Strake Shape (263-266, 7 00

271), YF-16 + 30.5 Stretch, LSF = 0 , M = 0.90

(a) Force and Moments, a = 10 (b) Increments, a : = 1 0 ' 4-46 Effect of Forebody Strake Shape (263;266, 702 271), YF-16 4- 30.5 Stretch, LEF = 25 , M = 0.90 (a) Force and Moments, oa = 2 5 ' (b) Increments, a = 25 4-47 Effect of Forebody Strake Size (Z72* 275, 704 Z80), YF-16 + 30.5 Stretch, LEF = 0 , M = 0.90 (a) Force and Moments, a = 1 0 ' (b) Increments, a = 1 0 ' LIST OF FIGURES (Continued) Figure T i t l e Page

-

4-48 E f f e c t o f Forebody S t r a k e S i z e ( i 7 2 , 0275, ZBO), YE'-16 + 30.5 S t r e t c h , LEF 4 25 ,

M - 0.90

(a) Force and Moments ,o a - 25'

(b) Increments, cu = 25

Effect sf Nose Strakes 273 and 274, YF-16 +

30.5 S t r e t c h , EEB = 0 , M = 0.90

E f f e c t of Nose StrakesoZ73 and 274, YE'-16 +

30.5 S t r e t c h , LEF = 25 , M = 0 . 9 0

Effect of Canard S t r a k e s Z 1 D and 281, YF-16 +

30.5 S t r e t c h , LEF = 0 , M = '.' 90

E f f ~ c t of Canard S t r a k e s Z 1 D and 281, YF-16 +

3 0 . 5 Stretch, LEF = 2 5 ' . M = 0.90 Effect of Nose S t r a k e Zl.00, F016, M = 0.90 (a) Force and Moments, CY = 20 (b) F o r c e and Moments, a : = 25'

Effect of Nose Strake 2124, Fo16, M - 1 . 2 0

(a) Force and Moments, a = 20 (b) Force a n d Moments, a = 25 ( c ) Force and Moments, a = 3 0 '

Effect of Nose Strake 2124, g-16, M - 2.00

( a ) Force and Moments, a. = 0

(b) Force and Moments, cr - 1 0 '

Effect of Nose Strake 2128, F;16, M - 1.20

(a) Force and Moments, a = 20

(b) Force and Moments, a - 3 0 '

INTRODUCTIQN The YE'-16 and F-16 developmental wind tunnel t e s t program has been reviewed and a l l force data pertinent t o t h e design of forebody and nose s t r a k e s extracted. Volume I of t h i s r e - p o r t (NASA CR-3053) contains the s t r a k e geometrical descrip- t i o n s , general coments , representative d a t a , and the i n i t i a l a n a l y s i s e f f o r t s towards the development of design guides f o r the a p p l i c a t i o n of s t r a k e s t o f u t u r e a i r c r a f t . This volume contains a complete s e t of t h e s t r a k e data. A few b r i e f comments follow to o r i e n t the reader.

A l l geometrical data a r e supplied i n Section 3 of Volume I. Table 4 of Volume I i s duplicated in t h i s volume as Table 1. It summarizes the t e s t conditions f o r each s t r a k e configuration and shows the applicable f i g u r e numbers. A l l pitch data a r e r e f e r r e d t o the s t a b i l i t y a x i s system and a l l s i d e s l i p data a r e r e f e r r e d t o the body axis system. Co- e f f i c i e n t s a r e referenced t o an area of 26 square meters (280 square f e e t ) and 25 percent of the mean aerodyaniic wing chord unless otherwise noted. Some of the l a t e r data a r e noted a s being referenced t o an area of 2 7 . 9 square meters (300 square f e e t ) a ~ d 35 percent of t h e mean aerodynamic wing chord, The dara a r e separated i n t o four s e c t i o n s ; low-speed p i t c h , low-speed s i d e s l i p , transonic p i t c h , and transonic s i d e s l i p . They a r e presented i n a comparative p l o t format.

Strakes a r e compared t o strake-off configurations when a v a i l - a b l e ; otherwise, they a r e compared t o other s t r a k e s of the same family. Within each section t h e data a r e presented by s t r a k e designation number i n ascending order within the l i m i t s of the comparative p l o t format. Incremental p l o t s a r e included f o r selected comparisons.

Table 1 (continued) Table I (~ontinued) trvres : (1) C u n t l ~ u f n r l o n ~ have s i n ~ ? t vertlcnl t a l l tlnlcas noted as tvln vcrtlcal (N) (2) 7hs YP-16 f ~ ~ a e l n g e wan ntratched 25.4 cm (10 In) f o r che F-16 1. L O W SPEED PITCEi DATA Figure 1-1 Effect of Slotted Strake Z22A, Configuration 401F-5, HT=O (a) Eif t and Pitching Moment B, Ec 8 . 2 8.q B . 6 b. B I .@ 1.4 1 - 6 I .f? 2.8 2 2 Figure 1-2 (b) Drag -18 8 10 U 0 6 0 j0.4 t 6 . 2 -0.2 - 0 . 1 1 R N G L E ' ; F R T ~ R C K . DEGREES" P I T ~ H ~ I I O I I . COEF .

Figure 1-2 Effect of Slotted Strake Z22A,,Configuration 401F-5, HT=-10 (a) Lift and Pitching Moment 5 . 1 , . . I . , ...................... .......... . )"' .,".<",.. ,,a,..., ".." , . p . = ; : : : h" .." 1 :..8y,o.#.:. ..!.......... j . . . ............... .. I.,, ,- . . " a s,,., t .......--.. I .... ...-. i... -....-... 1 . . . . . . . . . . . . I . . . . . . a , . . . . ... .,..".&..I ..-. . -.. ............. :."..L .......-* .( .-.,.,,,.,). I a- .......-........*... "* .""..-..,.. "..,...", ..,- ."...." ........... ". " ..... .-..-.. .... ,....- .................................. ".....I..._ - .-.., -.." ---.- ..---..* -,..-"I.-~..,. ji'-.; ..... -..- I... " ..-. .. ".".-..... ..-a ..-.,.. ..-.,.... q".

1.- -*.-.,.. ..-......-.. ..",..; .........- i - . . . . , . , . . ,.." .,..- ......... " - ...........-......-. "...

I I i .r.

......-................. ",* ...-, ^ .- ...,........ " ,./.-,_ .-,.. "_" . ......... .., ....(. - I , I *"' - "'"""", ' 1 """ "' " I "' ' " ' 0 "' 1 -1 0 B 18 68 t 9 . Y 19.2 -8.2 -0-ti R N G L E ~ ~ D F R T T ~ R C K , ~EGKEES" P IT&'NOH. COEF .

Figure 1-3 Effect o f S l o t t e d Strake Z29A, Configuration 401F-16 (a) Lift and P i t c h i n g Moment Figure 1-4 Effect of Rotating Strakes t 3 3 A ' and ~ 3 3 ~ ' , Conftguration 401F-16 (a) Lift and Pitching Moment -10 0 1 8 68 +@.4 +6.2 -6.2 -@.I!

R N G L E ~ ~ F R T ~ A C K , D?GREES~' P 1 ~ ~ ~ ~ ~ 0 1 1 . COEF .

Figure 1-5 Effect o f Rotating Strakes Z33A-Z33D, Configuration 401F-16 (a) Lift and Pitching Moment -10 0 18 80 t 0 . U t 0 . 2 0 . 0 -6.2 - 8 . V RNGLE~BOF GTGCK, D Y E B G R E E s ~ ~ PITCH MOM. COEF.

Figure 1-6 Effect of Rotating Strakes Z33E-Z33H, Configuration h01E-16 (a) L i f t and Pitching Moment LIFT COEF.

- 0 . '+ 8. Y 8 . 8 1.2 1 .S 2 . 0 - 1 0 e 10 60 te.4 r e . 2 - 0 . 2 -O.Y - FINGLE~~OF R T ~ ~ C K , ~ C G R E E S ' ~ PITC%~MOII. COEF .

E f f e c t of Rotating Strakes Z33C and 2332, Configuration 401F-16 Figure 1 - 7 (a) L i f t and Pitching Moment Figure 1-8 E f E e c t of Farebody Strakes 233 and Z50, Conf iguratian 401F-16, LEF=I!

[a) Lift and Pf tching l%ment: . . . . .

..l* , . . . . r . . 6 -*,.- . , . . u . . . . - I .-% r ,,-*,,,*- .*,*...a ..I.. ..,,* ..-,-. .... ".".." .,,.,.. *.., ..... .*...*".,. ,.?. . l..,'.. .I.r*..* ..... ,l.,,I,.,"..

2 .... -- ..-. ibq . , , , . . , . . , , . ...- ".. ,.I.,... ".,,, .*,<.,.-.' ..,-*a. .... .,.,..* ..... "",* . . . , . ,,.." .,,...... ",.,r.-,],. .............. - - c t , . * ....

"..".."r ",--"."I Il,*".."...l

. . I t

;-.+ .&...;,.. -....k:* : L : : : : ~ : e : : : ; : l : : ; : = . . ; : : : : : : I x : : : : : : ; : t ; : : : ; : : : ::::::::I:~:...:::::l~::;:::C::~: . : : : : : x i . :l ............. . . . ; . a , . .

.*..*-..I,. .......... .,..&* ............. ..I..,.. -,,.,\..",,. .. . . A 9 . <1.... .... l , , " . U . , .............................. .1,..111" .,., .................... ".

-.,,.s..4 ..,.. r,.... *L---.* ..I.. -1. ..*.-.,-. "L-.*",.. I ) , , , ..-..a .... ".*..,..... ,,,*",.I , . . . ..ll,,.!,l-.l .(..*..,"... .u.~.. * * . . / l l . ,,-..-. *, ...-,.,. *,.

w . 1 . 8 l . S . .*.-.,I.. "..I- . 3-. I... . .,."..*..,.. ..". .," .... , . , , . , . .... ....,*..,.. . . . . " .,,., "L." ..,..,. . , , . ...., . -..... ;,.."..-"I..,..

F - k 4 ." ................... 4 . h . ......... *" r ..... i, i"l ."'",.,* ! . ." ...-.,.,,.. ".,,"""'.",, , ""' "1"'"".*"'.. i """."'.',.. .'..."""". - 1 0. '4.' '...*". :." ..... *.'y' "".',#',a,. ...

I- LL'?

k e l -1 Strakes 233 and Z S O , Configuration 401F-16, L E F = ~ ~ O E f f e c t of Forebod Figlrre 1-9

(a) L i f t and P L t c i: ing Moment

I -10 0 10 68 t 0 . 4 4 8 . 2 -0.4 R N G L E ~ ~ F R T ~ ~ C K . ~"E"GREEs'' P I T C ~ ~ M O M . - 0 i ; 2 0 ~ ~ .

Figure 1-10 E f f e c t of Forebody Strakes 255 and 256, YF-16 (a) L i f t and P i t c h i n g Moment -..

-zz-J . .

i - 4 i i.i i i I J 2 J - 2 : . .

-- - - .

s i : , - --- . -. - - . .

' T I ' - .-:: .--- llif S S Z Z . i: :? 3-2 i.:l : ? I : s - 1 , ....

?'?I?

".?f F 7 7 ;: . a * !

. . . .

,,I, -...

I ? ? !

i ! ; !

I * , I ! i i 5 i ! !?

-

,.a<.$ i

!i<f -

. . - . 8 : . : < .

....

8 1 - 1 5 ; i.; !

....

.-.

. .

... : -.-.

i i i -

. . .- i s . ; , - . - .. .

...

' 7 : ; - ..-.

- l e 19 6 0 R N G L E ~ ~ F R T ~ ~ C K , D ? G R E E S ~ ~ i 8 . 4 t e . 2 PI T C ~ ' M D M .-Y?OEF. - 8 . 4 Figure 1-11 Effect of Large Rotatfng Strakes 257 and 258, YF-16 (a) L i f t and Pitching Moment I".".."... .".. a"*.. .,..... *,,, ... .1,^*.,%. , . " . * 6 . . . . .a..l*".l,.. "1,.,~-*.1.1.**.1..*~~. .... * ,.I.. .*.S.^."#., ., ,....,.,,. ..,.. (., . ...,.I.,., ..,.,... (,,(..

-"..-.. -.-. - -4-- "... __._..I.._ -,... - ...- .a.. -.- - ,.""

."" -... 4. ---..- ....).". "... -., ._..., _" , , . " l , ,, ,..,,.."

1 ---... 1 .-.,.. 4 ---- -t .. .. -,-.,..; -.....-. 1 .....,.... .--..,fa,,.-.-.. f -.---, 1 , . . * . , . i ... :- .I .....-.-.I -..,," A .,,..., ... ..-..- ....,..,..,. , . u . . . . . . . . r i..,. :... ..-... .. -. ,..-.... I . . . . . , . . . . ....... .. -........... .!....,.,.I., ,.....,. .. ,.,. .. .. . . .,... , t0.U t ' J . 2 €3.0 t -@.2 -<A 11 PZTCH WM. COEF.

~ i g u x e 1-12 Effect of Forebody Stxakes 263-266, PF-16 + 30.5 Stretch

(A) L i f t and Pitching Moment 0.4 8 . 6 0.8 1.0 1 . 2 1 . 4 1.6 1.8 2 . 0 2 - 2 DRRG C O E F .

Figure 1-12 (b) Drag ORIGINAL PAGE IS OF POOR QUALITY J e u- a*;

- 18 10

ANGLP'OF FITSTBACK. FEGREE?

Figure 1-12 (c) ~ncrements I a 6 e S B . ~ I i e . 2 - 0 . 2 -c.* R N G ~ - E ~ ~ F A T T ~ R C K , ~ ~ G R E E S ' ~ P J T C ~ ~ ~ I O M . ~ COEF.

E f f e c t of Forebody S t r a k e s 267-270, YF-16 + 44.5 S t r e t c h

r'igure 1-13 (a) E F f e: and P i t c h i n g Moment 0.6 0 . 8 1 . 0 1 . 4 DRRG ' ~ O E F .

Figure 1-13 (b) Drag 6680 56 25 0 B 6 . 2 a zti7

- 6620 51 2s B 0 0.20 zca

Figure 1-18 ( c ) Increments I - LL?

He .J

-1e 9 I e zo 30 60 +e.lr 1 . 0 . 2 -8.2 - e - 1 1

PI T C ~ ~ M O M . COEF .

RNGLE O F RTSRCK, ~ ~ G R E E S " Figure 1-14 Effect of Horizontal Tail Deflection with Strakes 263 and

- 2 6 6 , TF-16 + j30.5 S t r e t c h , TXFeO

6) *-Lift and ~ l t c h f n i &-mnt l

I .e 1.2 1 - Y ORFIG COEF.

Figure 1-14 (b) Drag Figure 1-15 , E f f e c t of ~orizont!al T a i l Deflection w i t h Strakes 263 and

2 6 6 , YF-16 + 30.5 S t r e t c h , L E F = ~ ~ '

(a) L i f t and pitching ~ o m d n t 8 . 8 0 - 4 8 . 6 8. I3 1 . 0 1 . 2 1.9 1.6 1 - 8 2 - 0 2-2 DRRG C O E F .

Figure 1-15 (b) Drag ORIGINAL PAGE IS OF POOR QUALITY -10 B i 0

RNGLP~OF RTTRCK, FEBEGREESS'

Figure 1-1.

syn rEsr R U N LEF TEF HT MUCH C O N F I G m*m ~ 6 2 0 i ~ 4 2s 0 2s B . 20 z63

- 6628 118 ES 0 25 0 . 5 2 266

*** BRSELINE RUN .

\ . .

.<" .,;..:,+.?.. .."..;.;..". ..?. le..;,, ,.;..:..:.;.. . . c . - . : . : . . ..,..;;..i.. ..;..;..j..: , s.i.,/..i..i.. .,a,. &..i.i, ..*.. r u . . i . . ,is.r 3 . ! s e f ..;., . a i..;...:.. ..;..; . . e . . t . . ..bi.i+.i..

.+.. ,,i..~.-2.. ...A ....,.. , . i . i l ~ . . l " ..*.*..I.. ..;.i.:.i.. ..i.;i..,.. ..l.i..'..i..

. , . . . L . , . & , . ,+-.i..i.. ..-L.:..;.. . * i s . ! . $..I..

,.i..; .,-. 4 . . . , > L . ; .?..

. a

-1 e 0 10 A N c ~ ~ 2 0 0 ~ R T ~ R C K . IYEGREES~' 6 0

Figure 1-15 ( d ) Increments, HT-25' . .

0 . 6 8.3 1 . 0 1 . 2 l .t( DRRG C O E F .

Figure 1-15 (b) D ~ a g I

- 10 0 10

RNGLEZ~OF QTYQCK, FEGREE?

Figure 1-16 ( c ) Increments 1 : w -16 6 I D 3 0 60 + & - I ! f e . 2 -8.2 - 0 . w PI ~c!i@t.;o~. CDEF .

R N G L E ~ ~ F FITTRCK . DF?GREES"

Figure 1-17 E f f e c t of F u s e l a g e S t r e t c h , 264 ( 3 0 . 5 Stretch) and .268 ( 4 4 . 5 Stretrch), LEFmO (a) L i f t and P i t c h t n g Moment 0 . 6 8 - 8 1.a DRRO ~ O E F . 1.4 Figure 1-17 ($1 Drag C 3 . 4 0.6 0 . 8 1 . 8 1 . 2 1 ."4 DRQG COEF.

Figure 1-18 (b) Drag

- 10 0 10

R N G L E ~ ~ O F R T % C K , ~?EGREE;' Figure 1-18 ( c ) Increments 0 . 6 8 . 8 1.8 l . S I . Y ORFIG CQEF.

Figure 1-19 (b) Drag ORIGINAL PAGE IS OF POOXt QUALITY 0 . 6 8 . 8 1.8 I . Y -1 .', 1 . 8 2 . 8 2.2 D R R G ' ~ O E F .

Figure 1-20 (b) Drag ORIGNAL PAGE IS QF Pmn QU"A.LPTY B a'?

0 s a t -10 B 10

R N G L E ~ ~ O F RT?RCK, FEGREE?'

Figure 1-20 ( c ) Increments 8 . 8 1 . 0 1 . 4 DRAG &EF.

Figure 1-21 (by Drag a .

t- J e w- o o ; F i g u r e 1-21 ( c ) . Increments ~ i ~ u r e 1-22 Effect of Nose Strake 276, YF-16, HT=25* (a) Lift and $if ching Moment Figure 1-22 (b) Drag -1" 0 10 26 '$0 BI? 6 B t0. 'I 40.2 ' 8 . 2 73.q P I I - C ~ ~ M O P ~ . COEF .

RNGLE OF RT%CK. DE.GREES Effect of Forebody Strake Forward Extent (ZS3, 264, 2721, YF-16 + 30.5 F i g u r e 1823 stretch, ' HT=O (a) ~ b £ t and Pitching Moment C s . 2 9-P( 8 . 6 0 . 8 'L .8 1 - 2 1 . B 1 . 6 1.8 2.0 2.2 DRRG C O E F .

Ftgure 1-23 (b) Drag ORIGINAL PAGE IS OF POOP, QUALITY -18 w- o l d \ Figt re 1-23 ( c ) Increments

t

Figure 1-24 E f f e c t of Forebody Skrake Forward Extent ( 2 6 3 , 264, Z72) ,kyF-16 + 3 0 . 5 .

B t r e t c h , HT-25O (a) Lift and P i t c h i n g Moment ~1.8 1.8 DRRG '&IEF. I - Y Figure 1-24 (b) Drag Figure 1-24 ( c ) Increments

Effect of Nose Strake 274, YP'q16 + 3 0 . 5 stretch

P i p r e 1-25 [a) Lifr and P i t c h i k g Element: Figure 1-25 (b) Drag

-%- , ~ 6 ' 4 0 :6e -25 : 9 1 6 : 0.2:~ + Z B ~

. re.-. 6648 - 3 8 . . -25 . . I?. . . . A . . . .@..a. &.WU. . .

Effect o f Nose, 274, and Canard, 524, Strakes, YF-16 + 30.5 Figure 1-26 Stretch, HT=O (a) LLft and Pitching Moment Figure 1-26 (b) Drag = !

7' -19 Q 18 ' 6 0 t B . 4 -49 2 ' 0.3 -@.'l PITCY'MOM. COEF.

RNGLE'@OF F I T ~ ~ C K , D!$GREES~~

Effect of Canard S t r a k e 284, YF-16 + 30.5

Figure 1-27 S t r e t c h , ~ ' E = 2 5 ~ ( A ) L i £ t and Pitching Moment Figure 1-27Qb) Dzag 0 1 e 29 3 e se r o 60 S O . * i a . 2 - 0.2 -9.w HNGLE OF R T T ~ C K , OEGREES P I T?H'MOM. COEF.

E f f e c t of Forebody Strake Shape ( 2 7 5 , 280, 287), YF-16 + 30.5

Figure 1-28 S t r e t c h , HT-0 (a) ~ i f t and ~ i t c t i i n ~ Moment B.0 0.2 0 . Y 0 . 6 0 . 8 1.8 1.2 1 . 4 1.6 1 . 8 2.0 2 - 2 DRRG COEF.

Figure 1-28 (b) Drag *r* 6640 76 2s 0 0 0.20 27s 6640 86 25 0 0 B . 2 b Z80 ----. 66W 12125 0 0 8.20 257 r m k BRSELINE RUN Figure 1-28 ( c ) Increments 10 2 8 3 0 4 0 EB 68 RNGLE OF R T T R C K , DEGREES

E f f e c t o f Forebody Strake Shape (275, 280, 287), Y E - 1 6 + 3 0 . 5

Figure 1-29 S t r e t c h , ~ ~ ~ 2 5 ~ (a) Lift and Pitching Moment e. E 8 . 8 1 . % 1.2 1 . 4 DRHG COEF.

Figure i-29 (b) Drag; SYP1 I'ERI' RUN LRP TEF \IT NnCn FONFIQ a @ w 75 88 P $s O.CQ ZSEI

- fiGhP R4 B5 @ CS 0.28

Effect of Forebody Strake 287, YF-16 + 30.5 Stretch

Figure 1-30 (a) Ltf t and Pitching Moment 8 1.8 1.2 I D R Q G COEF.

Figure 1-30 (b) Drag 19 3 0 6 8 R N G L E ~ ~ O F RTTRCK. C?!GREES~~

2 %

Effect of Forebody Strake Shape (288 and Z89), YF-16 + 30.5 S t r e t c h

Figure 1-31 (a) L i f t and PFtchFng Moment o 4 Figure 1-31 (b) Drag ?

P -10 0 10 68 to .Y t0.2 B.Q -8.2 -8.9

RNGLE'CF R T ? ~ C K , ~ ~ G R E E S ~ ~

P I T C H MOM. COEF.

Figure 1-32 Effect of Forebody Strake Forward Extent (263, 287, 2101, glob), YF-16 +

30.5 Stretch, HT-0 (a) Lift and Pitching Moment 0.6 0 . 8 1.0 1 . 4 DRRG ~ O E F .

Figure 1-32 (b) Drag $ ORIGINAL PAGE IS

OF rwn QUALIW

-10 0 10

ANGLE~"OF RT%CK, PEGREES~'

F i g u r e 1-32 ( c ) Increments Figure 1-33 Effect of Fmebody Strake Forward Extent (263, 287, 2101, 21061, YF-16 f - - 4 - 3 0 . 5 Stretch, H T = ~ S O -- (a) Z i f t and P i t c h i n g ~ o m e n t ' 0. R 1 .e 1 . Y D R R G ' 6 3 ~ ~ .

Figure 1-33 (b) Drag w- o r d Figure 1-33 . . (c) Increments

- _ -.-- - - -

Figure 1-34 E f f e c t of Nose Strake 2100, YF-16 (a) L i f t and P i t c h i n g M o m e n t 0 . 8 1.8 1.2 1 .1( 1.6 1 . 8 2.8 2.2 D R R G COEF.

Figure 1-34 (b) hrag Effect of Hori-zoptal Tgil Deflectio'n with Strake Figure 1-35 2103 F-16 with Wing W38B . ' (a) i i ~ t and pitching Moment; J 6. B 8 - 2 8-4 8.6 8 - 8 1.0 1-2 1 . Y 1.6 1 - 8 2.9 2 . 2 DRQG COEF.

Figure 1-35 (b) Drag 0 - 8 1.6 I -Y.

DRRG 'ZOEF.

Figure 1-36 (b) Drag

- 1 8 e la i e .r +B.Z 'e.2 - 9 . u

gs

R~,~GLE'%F R T $ ~ C K , DEGEEES"

~17Ch~~h31.1. COEF.

7-3

- % D

w ~ i ~ u r e 1-37 E f f e c t of Forebody Strake S i z e (2103-2105). F-16 w i t h Wing V3BB, HT-25" 4% (a) L i f t and PfFchLng Moment 8.2 O . Y 8 . 6 8 . 8 1.0 i .'I DRRG ' ZOEF .

Figure 1-37 (b) Drag Figure 1-38 Effect of Horizontal T a i l Deflection with Strake 2103, P-16 with Wing W24 (a) L i f t and P i t c k i n g Moment Figure 1-38 (b-1 Drag Effect of Forebody Strake Size (2103-2105), F-16 with Wing W 2 4 , HT=O Frgure 1-39 (a) L i f t and Pitching Moment Figure 1-39 ( . b ) Drag -18 0 10 60 +0.4 t o . 2 -8.2 -0.4 PI T C ~ @ M O M . COEF.

A N G L E ~ ~ F AT%CK. DYGREES"

Figure 1-40 Effect of Forebody Strake Size (2103-2105). F-16 with - Wing W24, HT=+~SO- (a).Lift and Pitching Moment Figure 1-40 (b) Drag - 0 . 2 -0.4 Q 18 6B r8.4 48.2 P I TC~'HOPI. COEF .

RNGLE'BOF Q T T ~ R C K , ~ ' ~ " G R E E s ~ '

F i g u r e 1-41 Effect of Forebody Strake Shape (2103, 2107-2109) ,F-26 with Iling WZ (a) ~ i f t and Pitching lfoment Figure 1-42 Effect of Forebody Strake Fcrwaxd Extent (2103, Z109) with Nose Strake 2112, F-16 w i t h %?ing W 2 4 (a) L i f t and Pitching Moment Figure 1-42 (b) Drag E f f e c t of Forebody S t r a k e Shape (2103,2107-2109) with Hose S t r a k e 2112, Figure 1-43 F-16 with Wing W24 (a) L i f t and Pitching Moment Figure 1-43 (b) Drag Figure 1-44 Effect of Nose Strake 2112 with Forebody Strake 2103, F-16 with Wing W24 (a) L i f t and Pitching -Moment I;" W" a I- LL* H e -I 0.4 8 . 6 0 . 8 1.0 1 . Y 1.6 1 . 8 2 - @ 2- 2 D R R G ~ O E F .

Figure 1-44 (b) Drag ~ i g u r e 1-45 Effect of Nose Strake 2112 with Forebody Strake ~ 1 0 9 , F-16 with Wing W24 (a) Liit and Pitching Moment I- LL?

? ' a -I 9 . B 6.2 * 0 . Y 8.8 8 . 8 1.8 1.2 1 .V 1.6 1.8 2.8 2.2 DRgG COEF.

Figure 1-45 (b) Drag Figure 1-46 Effect of Canard Strake 279, F-16 (a) L i f t and Pitching Moment I - LL?

' + t B J 8 . 6 8 . 8 1 . 0 1 - 2 1 - 4 DRQG C O E F .

Figure 1-46 (b) Drag I- LL?

H a ?

J Figure 1-47 Effect of Nose Strake 2124 with Nose Probe, F-16 w i t h Wing U 2 4 (a) L i f t and pitching Moment I-' t - ' Q\ Figure 1-47 (b) Drag 1 e 3 2 R N G L E ~ ~ O F RTTRCK , $ G R E E S ~ ~ Figure 1-48 Effect of Nose Strake 2124 without Nose Probe, F-16 with Wing W24 (a) Lift and Pitching Noment t - ' t - ' 0.4 8 . 6 6.8 1 . 0 1.2 1 . 't 1.6 1 . 8 2.8 2.2 v DRRG C O E F .

Ffgure 1 - 4 8 (b) Drag Figure 1-49 Effect of Nose Strake 2124, F-16, HT=O (a) ~ i £ t and Pitching Moment Figure 1-49 (b) Drag

I" 69 +a .s +8.2 - 8.2 -0.u

RNGLE'CF O T ~ &CK , $!GE~GREES~' P I T C ~ ~ M O ~ ~ . COEF.

Figure 1-50 Effect of Nose Strake 2124, F-16, HT= +25* (a) Lift and Pitching Moment 8.2 8 . 4 8 . 6 0 . 8 1.8 1 - 4 1.6 2.8 2- 2 DRRG 'GOEF.

l?igure 1-50 (b) Drag I- LL?

-m A t B - 0 t@ .2 -9.2 'B.Y P I T C ~ ~ M O M . COEF .

Figure 1-51 Effect of Nose Strakes 2123-2127, F-16 (a) Lift and Pitching Moment I- LL?

H I 3 -1 Figure 1-51 (b) Drag Figure 1-52 Effect of Nose Strake Inclination (2124 and Z128), F-16 (a) Lift and Pitching Moment 8.8 1.8 1 . 2 1 .'4 DRfW C O E F .

Figure 1-52 (b) Drag 8 10 60 18.4 10.2 -0.4 RNGLE"OF R T ~ R C K . $ ~ G R G R E E S ~ ' P I T&'MOM ~'~='oEF.

Figure 1-53 Effect of Nose S t r a k e Length (ZL31,Z131A and Z131B), F-16 (a) Lift and P i t c h i n g Moment t - ho!

t-rg -1 8.8 8.2 8.F 8.6 B . 8 I .tJ 1 . Y 1.6 1.0 2.8 2.2 DRRG 'SOEF.

Figure 1-53 (b) Drag rff .2 - 0 . 2 - 0 . Y -1s e t e 20 30 60 4 0 . 4 ANGLE OF RTTRCK. ~ " E ' G R E E S ~ ~ P I T C ~ ~ M O M . COEF .

Figure 1-54 Effect of Nose Strakes 2131 and 2132, F-16 (a) L i f t and Pitching Moment UN LEF TEF HT WRCH -&- 6901 128 25 0 9 8.28 OFF 10 60 48.4 40.2 0.9 -8.2 - 0 . 4 P I T C H M O M . COEF.

QNGLE~BOF QTGCK, D"$GREES~@

Figure 1-55 Effect of Nose Strake 2133, F-16 (a) L i f t and Pitching Moment 18 68 ti.4 te.2

P I T&'PIOM ;'ZOEF. -0.11 QNGLE'LF IJV-%CK. D";GREES~~

Figure 1-50 Effect of Nose Shape, F-16 (a) L i f t and Pitching Moment ~ u r m u l u , J N W N N 8'2 9 ' 1 Z ' f

A303 lzfl

2. L O W SPEED SIDESLIP DATA

-15 -I B - 5 5 26

RNGLE ? I F S 1 DESL 1 P , " D E G R E ~ S Figure 2-1 .. - . E f f e c t of Forebody Strakes ~ 3 3 and - - . . - - ..

OItIG1NAL PAGE It-

OF POOR Q U U l Y

Figure 2 - 1 (b) F o r r e and Moments, a =:)lo -15 -10 -5 B 5 18 : 5 20 QNGLE O F S I D E S L I P , DEGREES Figure 2 - 2 E f f e c t a f Forebody Strakes 2 6 3 - 2 6 0 , YF-10

+ 3 0 . 5 S t r e t c h

[a) F o r c e 2r?b M o n e n t s , a=26 - .. ,--- -- , .

Figure 2-2 (b) Increments, a = 26' ( c ) . -. . . --"---- Force and .- r{o_ment.s-, . p = 3 2 - ' * Figure .--. -. 2-2 -.. .

**a 6620 38 25 0 0 31.5 (I. 20 Z69 6620 34 25 0 0 31.5 0 . 2 8 164 6 6 2 8 Y 2 25 0 B 31.5 0.20 265

- 15 - 18 -5

RNGLE BOF SIDESLIP, "DEGREE

Figure 2-3, (d) Increments, a =320 C3 zm w ?

j : Q

E* -

- 15 -1e -5 15

RNGLE $F s I DESL I P , ' ~ E G R E E S

F i g u r e 2 - 2 (e) Force and Moments, a = 3 6 ' - ..

- - . .. ..--- --.--.-. -. . - -. . .. - ORIGINAL PAGE TS OF POOR QUALITY Figure 2-2 (f) Increments, a = 36' Figure 2 - 3 Effect of F o r e b ~ d y , -$trrake Forward Extent

(263 , ~ 6 4 , . 2 7 2 ) , YF-16 + '30 - 5 S t r e t c h

(a) Fqrce ---- and Momqfg - , , 9 = 2 7 ' Vn,PUIlYCLU r nvTu LC> OF POOR QUALITY Figuse 2- 3 . (b) Increments, a &i'.7'

(c) Force and Moments, a - 33'

Figure 2 - 3 -

ORIGINAL PAGE 1s

OF POOR Q U A L I ~ Figure 2-3 (d) Increments, a =33' Q Figure 2 - 5 ( e ) F Q X ~ and Ifonlent$, a =37 ORIGINAL PAGE I S OF POOR QUALITY SYtl TEST R U N LEF TEF HT RLPHR MllCil CO?.!FIG *** 664863 25 0 0 37.V 0 . 2 0 Ze3 0 . 2 3 I B l i 66u@ 12925 0 0 37.11 66110 73 25 8 0 36.5 0.20 772

-15 -10 -S QNGLE BOF SIDSESLIP, 10 DEGREES 15

Figure 2 - 3 ( f ) Increments, a = 3 7 O -IS -5 : < 0

RNGLE b~ S I D ~ S L ~ P . J O ~ ~ ~ ~ ~ k ? ~

Figure 2-4 Effect of Strake Size (263 and 2661, YF-16 +

3 Q , 5 Stretch (a) Force and Foments, a = ~ 6 ~ ORIGINAL PAGE I S OF POOR QUALITY Figure 2-4 (b) Force and Momcnts. U =32 Figure 2-4 (c) F o r c e and f!oments. a '36' ORlGINAt PAGE I 9 OF POOR QUALITY

2 6 3 , YF-16 + 30.5 S t r e t c h

(a) Force and Ploments , CY =26' Figure 2-5 (b) Force and Moments, u -32' . .

.... .... ." . . 5 . 1 . ..i i ...i . 1 . . . ; . + . . a .i. .d..i..,.,i.. .;.i..i..i.. , i,.+.i . . . . ..;.,i..r..:., . . ! . . ; . - I . ! ..I.., .... .i.;..;.i..i.~ ‘..(.. ..;.I,, ........... ..!

..- . . . . . I , , . . ..

..I.] f . ; .

. : . ! . : . - I . . ..I..,..!.,:.. .i..i..:..i .:.. ,.+.+. : '..:.A. ....-.-.-.. .z.A..L.;.. ..,..- - .:,..., i.. ..a,., , I . .

: . . .

," ..,..:..,.. ...., .,..,., .:,.;.,i..; . .;.!"-.' ., .&i.i. ..;..:.:,$.. .i..i.+.;.. ....,. ;.,. .,., : .,.. . . . , . ,..i,, 4../ . . ; ..,..., i. .... i ....

, : ; , ;;.;,; ; . ; i .: , * . , . . a .

....... . t................ ..,.. p . i ...I.. .., ...F..i...l."..i i ........................... ..:..i .:..;..I-{.: ..i..i..+.+ .j..i.,.:..;.. ..i-;..pj.. i.*.<..i ,i ,.,,. ;.,i.. ....,.. ;..i ....., ,(..,...

. . . . . . . . . . . . . . . . . . . . . ( . . . . . . . .

' : . t . . . . 8 . , Y ' . .

-18 -5 0 5 10 15 20 QNGLE OF S I D E S L I P , DEGREES Figure 2-5 ( c ) Force and .Moments, ~ ~ 3 6 '

- 15 - 1 8 - 5 20

RNGLE BOF S I D S E S L I P , "DEGREPS

Effect of Vertical Tail w i t h Forebody Strake Figure 2-6

2 6 6 , YF-16 + 30.5 S t r e t c h

(a) Force and.qn_e_n_ts ,.=,=26° -1s - 10 -5 0 s 1 e 1s 20 ANGLE OF SIDESLIP, DEGREES Figure 216 (b) Force and Moments, a=32' -18 -5 20

RNGLE BOF S I D ~ S L I P , "DEGREE

Figure 2-6 (c) F o r c e and Moments, a 4 7 ' S I D E FORCE Y R W I N G MOMENT ROLLING MOMENT -8.19 -8.85 B.0B -9.18 -8.85 a.88 LI .e5 @.lei - B . B ~ -e.se -3-28 6-ee e-20 Figure 2-7 (b) In.clrements, a = 2 6 O - .

- 15 -16 -5 ' 0 15 20

R N G L E $F SID~ESLIP, "FGREES

Zigure 2 - 7 ( c ) F o r c e and Moments, a = 3 z 0

- 6 6 2 0 5 3 25 0 0 31.5 0,20 268

6 6 2 0 6 2 t?S O 0 3 1 , 6 0+20 269 6620 66 25 O 0 31.7 0.20 230 a** BRSELlNE RUN

-1s - s s 10 za

R N G L E ? I F S I D E S L I P , DEGREE

Figure 2-7 (d) Increments ,a= 3 2 ' ORIGINAL PAGE I S OF POOR & U r n C3 2" w?

A?'

J &(D L1

- 15 -18 -5

RNGLE BOF S I D ~ E S L I P , 'BDEGRES

Figure 2-7 ( e ) Force and Moments, 41=3y0

-1 B -ti R N G L E BOF S I D S E S L I P , 'OOEOREE 20

Figure 2-3 ( f ) Xncraments, ~ ~ 3 7 0 S l D E FORCE '-4 R O L L I N G MOMENT , e . ~ e - 0 . ~ 8 4 - 2 9 0.w e.20 t-" - 0 . 8 -B.85 8-80

2 . L

n " ' Pigure 2 - 8 (b) Force and lloment.s, a =32' F i g u r e 2 - 8 (c) Force and Moments, a = 3 7 O ..i.L.r,.i.. ,~i,-,".~,. ..h,,"tl*.. .~l.*.*~".< ..is..* ,,.,.. ,.,..I...,,., .* ,,(.l +s~?.) ,%! ,II.I?l ..! ,,,,1 j ,?,, .>I,, *, !, I<. .... l,"i,. ..a. A..! ..,I, ..+.? ,,,.,,,, ,.,..,,.. . . .. >,.:. il I ,. . ..I.

...-. T.,.. :,.-. ",, ..;.?,. ...,. . $ . , . ; ..,,. ,r .,.. '. .*. .,... .I.,F, '.L'l'.."t' \ . , , . . ; a , , , . . - . A , * * .,,- *. .*%. . . , A .I... 4.1 ,?%,i ..:. <,. .-,*.. ., n .,,\. ". ..r . .'

3 : ..rrA.. . * m ; + ..,.. .?+A .i.. ...sA. 4 . . ." .,,,..,.. . ...... .". ,+ ,,,.,.... .. ."..;. .,i ,*.- ..,.. ,.......,.... I......., . ....,.,.. : . .-.a .... i .... */... ; ... , .. ... .....,. . .., .,Lis*.tb. . l+l-I,. :t.i..+vl.q jw.w,.t,-./,.-i.i , . ~ . r _ 6 4 1 : , . . l - - l , . . . : .!~i.i.i$...~.~ .++.<..i.. ~ + . . ~ . ~ i . . ~ t . h i 1 i s .+.. , 1 . w . i . ,

-

- 15 - 1 0 - 5 s 1 e 1 5

RNGLE CF S I D E S L I P , DEGREES

F i g u r e 2-9 E f f e c t o f F u s e l a g e S t r e t c h , 264 and 268 (44.5 S t r e t c h ) (a) Force and Moments., -(r-:2C0 O R I G * ~ A L PAGE I S OF POOR QUALITY

- 18 - 5

RNGLE BOF S I D ~ S L I P ,"DEGRE&

Figure 2-9 (b) Force and Moments. 0r=32' Figure 2-9 (c) Force and floments, a =36' r- R O L L I N G MOMENT Y Q W I N G MOMENT SlDE FORCE 09- -8.18 -9.95 ~ . e e -8.19 -8.85 8.98 8.95 8.10 -8.68 - 9 -e.28 8-86 8.26 2 :!

figure 2-10 (b) Tqrce and Mqpcnts, a =11° ?m H ?

j r

-15 -18 - S 15 20

RNGLE SF SIDESLIP, "DECREES

Figure 2-11 E f f e c t of Nose, 274, and Canard, 284,

Strakes, SF-16 + 30.5 S t r e t c h

(a) Force and Moments, a =27' Figure 2-11 (b).' Force. and Moments, 0'33' I -15 -10 -5 20

RNGLE BOF S I D ~ S L I P , " D E G R E ~ ~

F i g u r e 2- 1 2 Effect of Forebody S t r a k e Shape ( 2 7 5 , 2 8 0 , 2 8 7 ) , YF-16+30.5 S t r e t c h

(a) Force . ..... a and omen^^, a=270

+In Z" us' x II F i g u r e 2-12 ( b ) Force and Moments, 4 ~ 3 3 ' SYH TEST RUN LEF TEF HT RLPHFl HACH CONFIG -8-- 66W 79 25 0 0 36.6 5.25 275 0 0 36.7 0 . 2 0 I80 *-B).- 6640 83 25 .-@-. 6640 124 25 0 0 3 7 , 5 6 . 2 8 287 Figure 2-12 ( c ) Force and Piornents, a=3T0 ORlGrNAL PAGE u3 OF POOR QUA3;lTJY I

-is -10 - S ID

RNGCE OOF s ID%SLIP, OEGRE&

F i g u r e 2-13 Effect of Farebody Stsakc Size

(263 and 287) , YF-16 4-30.5 Stsetch

(a) Force and Noment s , "0

- 15 - 10 -5 2Q

RNGLE BOF SIDESLIP, ' ~ D E C R E ~

Figure 2-13 (b) Force and lloments, a =ll ORIGINAL PAGE 16 OF POOR QUALITY I-l = " : a+ l - - A W O m 6640 127 0 0 0 10.9 O+2Zi EJi "!

*l* BASELINE RUN

- .- -

-. ; -., ::/:;;:;-:;: , , ,;,;;;;:;::;. ..,... 1.; :; .!i,.~... ,c.:.y : . : ; ; i : i : ,!~+,~,,:,i ;~y:f . . , . . . I..,I,i.~. :,;:;;:i:;!;: :;':;"? i:i.ji[,::!,~.;.: ,:ib: 2:: < : : : : ; : ; ; : ,I.!,.?.,. ;;b;i:j:$-,;;:; ,,+,iiijjjj .r+...., (,--,:;$: . :,,.,,,..i..,.. :;I:;::;::- ,,.[r ;t;,;::; ,,. li : . . . ; . : - ... i ..,.+..+.A. ..... , . * .,.. . , t . ) . ' . ..)..,*.(.I*,. ~~. : &,.l%.i . . , > , . * I . ! . . ' . . 1. ..ll/~.!..(.. .

Il!..~..tl;l.~.)I!lf.f ...(.ly ).). . . .I...&. . 4 . . , " .A" . .,lpl . .l),J..;l (.. 1 , .!. . . I.. b* I : . I..:. J , . . . ;*..

-1s -10 a- 5 o s ga RNGLE O F S I D E S L I P , l @ D ~ ~ ~ ~ k k Figure 2-13 (c) Increments, a =11° - 15 -10 -5 16 1s 20

R N G L E BDF SIDESLIP, DEGREES

F i g u r e 2-14 Effect of Nose, 2 7 6 , and Canard, Z86, S t r a k e s , YF-16 U (a) Force and Moments, a = 2 7 -

-15 -18 - 5 20

RNGLE BOF S I D ~ E S L I P , '~EGREE

Figure 2-14 (b) Force and Moments, a = 3 3 0 Figure 2-14 (c) Force .and Moments, ~ 3 ~ 3 7 ' -4r 66403 25 0 0 26.9 0 . 2 0 OFF 25 6 3 0 27.0 0.20 277 -@-- 6640 8 --B 6640 12 25 0 0 27.0 0.2% Z79 -1s -10 -s

RNGLE BOF s IDSESL I P , "DEGREPS

Effect of Nose (277) and Canard (279,282) Figure 2-15 Strakes, YF-16 (a) Force and Moments. 0=27" -15 -10 - 5 0 5 10 15 72 A N G L E O F SIDESLIP, DEGREES Figure 2-15 (b) Increments, ~ 1 2 7 ' ORIGINAL PAGE IS OF POOR QLALI'IY.

-IS -10 - 5 20

. RNGLE BOF SIDSESLIP, '@DEGRE&

Figure 2-15 (c) Force and Moments, ~ ~ 3 3 ' I

-15 - 16 - 5 0 S i 0 15

QNGLE OF S I D E S L I P , LEGREES Figure 2-15 ( d ) Increments, a=33 m i a -5

FINGLE OOF S I Q ~ E S L I P, " D E G R E ~

Figuse 2-15 ( e ) Farce and Hamems , a 437'"

"'" i "'1""';", ,;:I"" ""'"' I"':''r.. I"""." ; 1'" ;'A, ' , 1

* ,,., , . $ . . ,,., * , . r ... *,a,* I , , *$*.. .,,,,>%.A,. r , . r , .

* . , + . . , , , . 3 * . . .

SYH TEST RUN LEF TEF HT RLPHR PlRCIl C0NFe!G *am 6 6 1 1 0 5 25 0 0 37.4 0.20 OFF

- G640 10 25 0 0 36.5 0 , C v 277

. . - . . . - 6640 14 25 0 0 96.6 0,ZO 278 I -15 -10 -5 16 20 R N G L E $F S?D%SLIP, D E G R E ~ ? ~ Figure 2 - 1 5 (f) Increments, cl=37' ORIGINAL PAGE IS OF POOR QUMtIW P W e ?I0 O m : r FFgure 2-16 E f f e c t of Forebody Strake Forward Extent (Z63,287,Z101,Z106), YF-16+30.5 S t r e t c h (a) Force and Foments. CY -26O -33 -1 4 -s P 5 18 15 RNGLE OF STBESLIP, DEGREES ORIGiNAL PAGE I S OF POOR QUALITY I- z u r n E : Z C) 2 : H .

3 '

i

-IS -10 - : ; 5 10 20 *

RNGLE @OF SIDESLIP, D E G ! ? E ~ Figure 2-17 Effect of Nose Stralce 2100, YF-16 (a) Force and Moments. =21° F i g u r e 2-17 (b) Force and Moments, a - 2 6 : ORIGINAL PAGE IS OF POOR QUALI%Y C n z 8 we: z z

- 15 -1B -S 10 20

R N G L E BOF SIDESLIP. DEGRE&

F i g u r e 2-17 ( c ) Force and Haments , a =32: Figu=e 2-17 ( d ) Force and Moments, a =37' ORIGINAL PAGE IS OF POOR QUALITY I -1s -10 - 5 20

RNGLE BOF S I D S E S L I P , ' B D E G R E ~ S S

FYgure 2-18 Effect of Forebody Strake Size (2103-Z105), F-16 with Wing W3BB (a) Force and Moments ,a=llu Figure 2- 18 ( b ) Force and Moments ,a=21° SIDE FORCE Y RW I NG MOMENT ROLLING MOMENT 1 - 0 . 0.ee -9.10 -@.W e.@@ a.05 8.1) - 0 . f ~ . - c . z ~ O ~ W 0.m -s 0 5 10 1s 2a RNGLE OF S I D E S L I P , DEGREES Effect of Farebody Strake Size (2103-2105), Figure 2-19 F-16 with WAng. W 2 4 I -15 -10 -s 20 RNGLE ?IF SID%SLIP, "DEGRE& E f f e c t of Wing with Forebody Strage 2103, F-16 Figure 2-20 (a) Force and Moments, O=O and 11 Sf OE FORCE ROLLING MOMENT YGIWING MOMENT -6.10 -8.85 3.09 8-65 8.18 -0.68 - 0 4 - 2 9 8.98 9.28 9 , -8.19 -9.~5 e.ee

* m-

a " ' P, a Q L L t d U I t

Pq

2?

r-( V) (f; TEST RUN LGF I'fX 111' F\LI3t1FI H X t I BONlPld G77P J ( t Q @ O D @R,h 0.QO 'i,l&9 i177(!97 26 R IF *Q,l Q,f18 RlQ3

!

0 0770 l l i j B & 0 1ir.Q n,Ca a l e 9 Figure 2-21 (b) Force and Moments, a-16 and 2 1 ' OliIGlNAI; PAGE I S OF POOR QUALITY l -1 5 - i e -5 20

ANGLE ? I F SIDSECLI P . ''DEGREPS

Figure 2 - 2 2 Effect of Forebody Strake Shape

(2103,2107-2109) , F-16 w i t h :inR H 2 4

(a) Force and Moments, =27 I -1s -ie - 5 s 10 1s 20 RNGLE ; F SIDESLIP, DEGREES (b) Fq_rcrc_a~d ~ o m e n t . ~ , . 0 632' Figure - .. .-. 2 - 2 2 ORIGINAL PAGE IS OF PBOf't QIXRLI'E F i g u r e 2-22 (c) Force and Moments, 01 =37 o I

-15 - l e - 5 0 5 10 15 20

QNGLE OF SIDESLIP, DEGREES Figure 2-22 ( d ) F~c.e-.and-Momen@, . a : 1 2 ' '=?

MOMENT Y R W I N G MOMENT S I D E FORCE : A . ROLLING -8.18 -8.65 8-89 -8.95 9.98 8-85 0.18 -8.68 - 8 . -e.28 0 . 0 0 OP I '=JG " o q H (D Figure 2- 23 (b) Forc-e gqd-.Molpent~. 4 132: SIDE FORCE ROLLING MOMENT YRWING MOMENT -8.18 -8.85 m e -13.10 -6.95 8.86 8-85 e.le -8.68 -8.w - e . m e . e ~ 8.29 I -IS -1e -5 20

RNGLE OF SIDESLIP, %EGRE&

Figure 2-23 (d) Fqrce and Mope.nts, (r=41° -15 -18 -5 20

RNGLE 8 0 ~ SID;SLIP, 1 0 ~ ~ ~ ~ ~ E ~

Figure 2 - 2 4 Effect of Nose Strakes 2110-2115, F-16

with Wing W?4..--

(a) Force gnd Moments, a 126" Figure 2 - 2 4 (b) Increments, ~ 3 2 6 ~ ORIGINAL PAGE .IS

oF PocjR QITALJT;Y

F i g u r e 2 - 2 4 ( c ) Force and Moments, a =32'

- 15 - 10 - 5 5 1 6 15

ANGLE ?IF SIDESL.IP , D E G R E E 8 Figure 2 - 2 4 ( d ) Increments, a =32O Figuse 2-24 (a) Forc:e and 1 4 0 m e n t s , c t =36' SYtl TEST RUN LEF TEF HT ALPHR MRCH CON wlrm 6771 4 0 25 0 8 36,7 0.20 Z l l 6771 21 25 0 0 36.4 @ , 2 B Ili 6771 U8 25 0 Q 36.4 0.20 Zll . - - - a 6771 25 25 0 0 36,4 0.20 Z118 6771 52 2s 0 0 36.4. 0.20 Z 1 1 4 6771 30 25 0 0 36.Y 0.20 5111 BASELINE RUN I J - I O a e?

m a I- W c

" ?

Q -1s -10 -5 0 5 10 15 2 C QNGLE OF SIDESLIP, DEGREES Figure 2 - 2 4 (E) Increments, G =36O

ORIGINAL PAGE IB

OF POOR Q U & ~ F i g u r e 2 - 2 4 (g)..Force and IZoments , a =41 I

- 15 - 10 - 5 20

RNGLE b~ S I DSESL I P , "DEGRE&

(h) Increments, crt =41° Figure 2 - 2 4 ROLLING MOMENT YRWING MOMENT SIDE FORCE +.$O -2-28 8-66 1 -8.85 8.00 -8.85 8.88 6 . ~ 5 Figure. 2 - 2 5 (b) Force and Moments, a=32.

ORlGINAL PAGE IS OF POOR QUALITY (c) Force and Moments .%a -36" Figure 2 - 2 5 Figure 2-25 (d) Force and Moments, a =41U ORIGINAL PAGE I S OF POOR QUALITY t-; jt

-

-15 - 1 e - 5 B 1e 15 20

QNGLE OF SI$ESLIP, DEGREES F i g u r e 2-26 Effect of Forebody Strakes 2120 and 2121 with C a n a r d Strake 2 7 9 , F-16 (a) ~ o r c e and Moments. ot = 2 7 . 3 0 a n d 32"

- 15 - 10 -5 26

RNGLE ; F SID%SLIP, "DEGRE& Figure 2:26 (b) Force and.bnents; a134; 3 7 and 42q --- - , - - .

ORIGWAL PAGE IS OF POOR QUAL,Im . . .

Effect of Nose Sfrake 2124, Fo16 Figure 2-27 (a) Force and Koments, a = -11 SYH TEST RUN LEF TEF HT RLPHA MACH CONFIG -&- 6811 218 8 9 8 -0.0 0.28 Z128 ..i.r.;..,. ..+,..i..~ ..;..pi. : . ..i..i..; t ..... ; ..... 1 . . ..,..;..;. .

e- 681 1 225 0 0 B 0. 0 0 .28 +~12r) lj:i:;:-!l:: :yj:z,:~: .:;:j:i?,k ;;:';,:; j ; : : , ; . . .

..,.. ."!"!.. .,+..i..i..", . . P $4 ..,.. ..i-i ..,. i. .,.I..,. .. . ,. , . ;.

. . . . . , -1s - l B -5 10 20

RNGLE BOF S I D ~ S L I P , DEGREFS

Fig-are 2-27 (b) ~ b r c e and Moments. a = 0 ' ORIGINAL PAGE IS OF PWR QUALITY . i e -5 0 5 20 .

ANGLE OF S I D E S L ~ P . ' $ Z G R E ~

Figure 2 - 2 7 (c) Force and Moments U =11° Figure 2-28 Effect of Nose S t r a k e 2124 with nose probe,

, F-16 with Wing W24

(a) Force and Mogen$s, a -25, 27 and 29' ORIGINAL PAGE IS OF POOR QUALIW I

-15 -10 -5 ANGLE @OF S I D ~ S L I P , '@DEGREE 20

Figure 2-28 , ( b ) Force and lloments, a=32; 36 and 4 0 ~ Figure 2-29 Effect of Nose Strake 2124 without nosg probe, F-16 w i t h Wing W24.

(a) For~.e._a_n_d_Moments,..a=25. 2 7 and 30" ' - ORIGmAI, PAGE IS OF POOR QUALITY

Figure 2-29 (b) Force and ~ o m e n t s ; a =32; 36 and 40

, (2124 and 2128), F-16

. ( a ) Force -an-LMoment~, a ~ 2 7 ~ sun TEST RUN LEF TEF HT RLPHR nncbl C ON FIG nu* 6811 s 2s B o 27.1 o . t a zlco 6811 30 25 0 0 27.1 0.20 t.Zi2V 4 I S L I 6811 48'425 0 0 27.1 0,ZO +Zl?c -15 -10 - 5 S 10 15 PQ R N G L E $F S I D E S L I P . DEGREES Figure 2-30 (b) Increments, a = 2 7

-1s - 1 e - s 20

RNGLE BOF s ID&L I P , '@DEGRE&

Figure 2-30 ( c ) Force and Moments. =32' ORIGINAL PAGE I S OF POOR QUALITY Figure 2-30 i d ) Increments. a = 3 2 ~ i g u r e 2-30

(e) Force and Moments, a - 3 7

ORIGINAL PAGE I S OF POOR QUALIW -15 - 1 B - 5 18 2 8

RNGLE BOF SIDSESLIP, DEGRE&

F i g u r e 2-30 (f) Increments, a=37 -15 -18 -5 5 10 15 20 RNGLE @OF S I D E S L I P , DEGREES F i g u r e 2-30 (g) . Force - and klqenttx, a=42' ORrfXNAL PAGE 19 OF POOR QUALITY -15 -10 -5 5 .- J 6 3 IS 23 RNGLE ?IF SIDESLIP. :lEGREES Figure 2-30 (h) Increments, a=42*

-10 . -5 0 5 18 15 28

ANGLE OF SIDESLIP, DEGREES Figure 2-31 Effect of Nose Strakes Z123;2127, F-16 (a) 3'prc.t-gnd Moments . - ~ 2 2 7 ORIGINAL PAGE I S OF POOR QUALITY 6811 4 6 4 2 5 0 0 2 7 . 1 6.20 .;El25 6811 411 25 0 0 27.1 8.20 +2126 L L .

W *, 6)

- 1 5 -10 - RNGLE 5 $F SID'ESLIP, 10 DEGREES 1s

Figure 2-31 (b) Increments, a=27 o I -IS -18 -5 28

R N G L E BOF SIDSESLIP, '@DEGRE&

Figure 2-31 ( c ) Force and llcments , a = 30' (d) Increments, a = 30' Figure 2-31 Figure 2-31 ( e ) Farce and Iloments , a = 32' ORIGINAL PAGE IS OF POOR QUA1;l'l'y J u r n a ' ?

(f) Increments, a = 32' Figure 2-31 3 7 O Figure 2-31 (g) Force and Plaments a " . . - . ---- 01ZIGINAL PAGE IS OF POOR QUALl'm Figure 2-31 (h) Increments, cY =37 Figure 2-31 (i) Force aqd Momentg , a =4z0 ORIGINAL PAGE 1s OF POOR QUALITY

-15 -10 -5 RNGLE BOF s IDSESL I P , IBDEGRE~SS

F i g u r e 2 - 3 1 (j) Increments, a = 4 2 O 6981 1 W 25 0 0 26.4 0.28 OFF

. . '-*- 6901 39 25 0 @ 25.4 0.20 2131

+-m. 6901 3W 25

I

+- 6961 29 25 0 0 26.q 0 . 2 0 2131B

, . . . . .

..t..i.+-..i.. ..;..r.i.i.. .&.i,i .i,. ..?..!..{..!.. ..?a .A. ?. ..i..t..a..a.. .I..i..c.+. ..is,& i. . , u . . ; . .1 ..... I..... ... .. i i . ,. ~..p,.. .... .....f. .... 8 . ....

.:.. L.I.:... . . L . ' . L . . ! . . ,.:..i,i .I" ....,.,.. ....... 4 . . . r , .;:..!..!..!.. ..:..!.,i..i. ../ ..... t . : . .. i .-..... ,+ ..-,-,:.. ,..r.7..'...;."..I... ..:.i . . . .: . . . - . . ,... ! I I : I ...... .... .. . . .... ........ ... ..... ../..+.+..;,. ..i + . ; . . 1 , . ..;. I . . ; . . { . . ..;.i ..-.. i..i ,.; ; :. .:..i..t.;. .,,.,..-.-. . . : . . a -.is. .L.- i..,.. ...-. J ..A ..,.. i $.. j ..: :.., ...*.. , . I . . . . . . !

. . ... .. ...I. . . .... . . I. ... ..,..l..r..,,-.v a~.r.+..r., . t l l l & st.. 1.. <I.~.~I~.I. "..! I <.. (.l.(?.s $..I. ..I<.$I.~.I*.. ..l.. #ll+.& Il.<l ( 3 % ) I .8v1.$ ..I. I L 1 t 1 : ,.I ) ) . . ( . I . k I I .1 . . , . . . .

-1s -18 - 5 0 5 10 15 QNCLE OF S I D E S L I P , DEGREES Figure 2-32 E f f e c t o f Nose Strake Length (Z131 ,Z131A1Z131B) , F-16 (a) Force and Moments, a =26" ORIGINAL PAGE I S OF POOR QUALITY SYM TEST RUN LEF T

* 6901 15 25 0 0 31.8 0.20 OFF

--e- 6901 40 85 0 0 31,6 0.20 El31 .-Bs 6901 35 25 0 8 31.6 0.20 Z131A a + - - 6901 30 0 0 31.6 8.20 21316 Figure 2 - 3 2 (c) Force and Moments, a =32' SYtl TEST RUM LEF TE'F NT RLPHR MRCH CONFIG **R 6901 15 25 0 6 31;s 0.20 OFF 6961 40 25 0 0 31.6 8.20 E l 3 1 .

6901 35 25 0 B 31.6 0 , 2 0 ZlSlR ," - -.

Reference conditions:- 27.87 mZ(300 f t 2 ) - Figure 2-32 ( d ) Increments, U =32' -4- 6901 16 ,2S B B 36.7 8.20 OFF .-e- 6001 (il 26 0 B 36.7 8.20 2131 .-m.

69'01 36 25 8 1 0 36.7 8.20 Z131R

-+ 68BJ. 3 1 25 0 0 36.7 8 . 2 0 Z131B

Figure 2-32 (e) Force and Moments, 4 ~ 3 7 ' F TEF HT RLPHA NFi 0 0 36.7 0 , 6901 36 25 0 0 36.7 0.20 2131R art are Figure 2-32 (f) Increments, a = 3 7 '

- 15 - 18 - S B 5 '9 15 26

GNGLE O F SIDESLIP, ,EGREES Figure 2 - 3 2 (g) Force and Moments. a - 3 9 ' *r* 6901 : . 7 25 8 8 38.7 0.20 DFF 0 8 38.7 0.28 Z l S i 6801 42 25 6981 37 25 0 8 38.7 0.20 Z131F1 Figure 2-32 (h) Increments, a = 3 g 0 Effect of Npse S t r n l c e s 2131 and 2132, F-3.6 FigUXa 2 - 3 3 a (a) Force and l\lomonts, Urn26 Figure 2 - 3 3 (b) Force and Moments, a =32' Fipura 2-33 ( e ) Force and Pfomsuts. am370 Figure 2 - 3 3 (d) Force and Moments, a =3gU I -15 -18 - 5 e 5 26 ANGLE OF SIDESLIP, " D E G R E ~ F i g u r e 2-34 E f f e c t of Nose S t r a k e Z133,0F-16 (a) Force and 'E?oments , a =26 I-n z e we: Z r W'n z'n O m : C F i g u r e 2 - 3 4 ( b ) Force and Moments, a=32_ -15 - 10 - S 10

RNGLE OF S I D E S L I P , DEGREFS

Figure 2 - 3 4 ( c ) Force and Moments. ~ = 3 7 ~ I -15 -141 hr; u 5 is t a RNOLE OF STDESLXP , ' ~ E O R E E S Figure 2 - 3 4 (ti) Force and Elomencs , ~ 2 3 9 ' F i g u r e 2 - 3 5 E f f e c t of Nose Shape, F-16 (a) Force and EIoinents , a=26 Wa, T O o m : E . .

- 15 -10 -S C 5 10 15 c 0 R N G L E OF SiCESLTF, DEGREES F i g u r e 2-35 (b) Force and Moments, a =320 -A- 6801 5 25 0 0 36.6 0.20 B A S I C 0 0 36.7 0.20 N7 --@-- 6981 16 25 .-&. 6B0l 21 25 0 0 36.7 0 . 2 0 N12 Figure 2 - 3 5 ( c ) Force and Moments, ~ = 3 7 ?

Figure 2-35 (d) Force and Moments, a = 3 g 0 Figure 2-36 Effect of Nose Strake 2131 yith Nose N 7 and Vertical Tail Off, F-16 (a) Force andtNoments, a=26"

- 15 - 1 0 - RNGLE 5 c OF S I D ~ S L I P , 1 0 D E G R E E S 1s

F i g u r e 2 - 3 6 ( b ) Force and Moments, a =32' -IS - 10 -5 B 5 10 15 RNGLE OF S I D E S L I P , DEGREES F i g u r e 2-,36 ( c ) Force and Moments, a =37 U 3;'ifi~11:o 2 - 3 0 (cl) X'QJ:GC and Plamants, ( ~ ~ 3 9 Figure 3-1 Effect of Canard S t r ~ k e 21, Configuration 401F-2 with T w i n V e r t i c a l T a t L s , M = 3.80 ( a ) L i f t and P i t c h i n g Moment 0 . 1 8 . 2 8 . 3 B . Y 8 . 5 0 . 7 e. e B.R 1.0 1 . 1 D R R G ~ ~ C I E F .

- Figure 3-1 (b) Drag, Large Scale I 0 - 6 0 8 . b2 b .0U 8,86 8.08 6.10 8.12 0 - IY @,L6 6.18 DRQG COEF.

F i g u r e 3 - 1 (c) Drag, Smald Scale Effect o f k z d L n g Edge Flap Deflection w t t h Canard Strake Piguy" 3-2

ZZk, Configuration 401Fr5, 14 - 0.80

(a) Lift and Pitching l4oment +I932 437 6 0 8 6.80 OFF 3 3 0 0.80 Z I R --Bf- 1832 516 10 6 8 9.80 Z l R 8 . 4 8 . 5 0.7 8.8 € 9 . 5 1.0 1 . 1 0 . 2 6.3 D R A G ~ ~ ~ O E F .

Figure 3-2 (b) Drag, Large S c a l e ......................... .', .....................I., c!l -. ................. .. -, ,.. , ..,. , ........ ..,. ~.. .,......

....... * r . . * ...... I.., .I... ,.*..I..... ....... b." ...I.. -

,...:...- ........ : .......-...... ................ " ..,........,.

L. z LL iL 5 .........-.\.. " ,.-.....-...., ; -..... " ........ " : . . " . $ " . . . 0 0 N ....... .....-... , ..,.. ..-. L.. '..",, U .*" .... ...,*....-..,.. * . .- ". .*. .". ," .. ...".... ..-., 8 . . a -.. .-..- .*. *. ..:. ... ......... . ...... .......

. , ....... ......... ......

*....a ..... .........

a * .

........

, ' r e 8 ....... I..

8.8 0 . I 0 . 2 0 . 3 B . B 9 . 5 0-7 0 . 8 0 . 9 1 . 0 1 . 1 DRI-IF ' ~ O E F .

Figure 3-3 ( b ) Drag, Large S c a l e Figure 3-4 Effect of Canard Serake Z l A , Configuration 40lF-5, LEP = 25', M = 0.80 (a) LZf t and Pitching l?oment I @ - 8 h 8.82 B,BW 8.12 8 . i4 B . 16 8.18 DPRG COEF.

Figure 3-4 (c) Drag, Smala Scale quamojg Z u ~ q 3 3 ~ d pue 12T1 ( e ) 08'0 = H ' ~ T T ~ J , TeaT2laA U J M S YqTM Z-JTOQ ~ 0 - f 7 ~ l f i 3 3 ~ 0 3 ' n z ayel?S p l E u e 3 30 2aa333 5-E azn81,d s33a33a ' Y ~ H L I B do ~ - I ~ N U 'A303 ' W O W H31Id h ' @ - I ' 0 - 8 ' 8 I * @ & SZ B 2 SI 0 1 S 8 S- e,e 8 - 1 9.2 e.3 B.Y e.5 DRRG B. COEF, B 6 -7 B.B 8.8 I .e 1.1 Figure 3-5 (b) Drag, Large Scale Effect o f Canard Strake Z l A , Configuration 401F-2 w i t h S i n g l e Figure 3-6

Vertical T a i l , M = 0.80

(a) L i f t and Pitching Moment 0.1 8.2 0.3 8.4 8.5 8.7 0 . 0 0 . 9 6 - 0 DRRG'POEF .

Figure 3 - 5 ( b ) Drag, Large Scale 1830 365 25 0 0 0 . 8 8 ZlFl DRRG COEF.

Figure 3 - 6 ( c ) Drag, S m a l l Scale I;" w- -6 6 ,5 ?H 4 0 . 4 48-2 6 - 0 - @ . 2 -C?.g RNGLE%F FITS&EK, I ~ ~ G R E E S " PITCM MOH, COEF.

Figure 35:7 Effect o f C a n a r d Strake Z l A , Configuration 4OlF-2 w i t h Twfn V e r t i c a l T a i l s , E l = 1.20 (a) L i f t and P L t c h i ~ g Moment e. B 0.1 0 . 2 8 . 3 8.4 8 . 5 B. 6 0.7 B.8 0 . 9 1.0 1 . 1 DRRG COEF.

Figure 3-7 ( b ) Drag, Large S c a l e .-*r .,el.. -r*r..,,rb ....-- . . .@,a...,"*r. ...-. 4. ." I..., ."., .-,,-.,. .C ....I *., .......

l > ~ : ; : : : r [ ~ h ; j : s : : : 7 j : " r : : t : . . . . . . . . . . . . . . . . 4 . . ;Z:.IZ:*::~ . . . . . . ,- x a Q I : ; ; : : . : , : * ] ; : : ; . : : : I*: ; : I . . <I::: , : : ; : , 1

...-#,l,.-,....... * . , ' " l....., .. ,rr

E f f e c t of ~ a n a k d S t r a k e 22, C o n f i g u r a t i o n 4 0 1 f 2 w i t h Twin Figure 3-8 Vertical T a i l s (a) Lift and P i t c h i n g Moment

I . . '. ' '

;;:.I * . 1 ; ; - . I

.--. ---- -& 1838 328 e B 9 B.88 OFF 9.B 0 . I 0 . 2 0.3 0.q 8.5 8.6 8-7 8.8 0.9 1-63 D R R G C O E F .

F i g u r e 3-8 (b) Drag, Large Scale Figure 3-8 ( c ) Drag, Small Scale 0.2 0 . 3 9.0 (b) Drag, Large Scale Figure 3-9 I- LL?

' - ' m -J

Effect of Canard Strake 23, Configuration 401F-4, M - 0.90

Figure 3-10 (a) Lift and P i t c h i n g Moment 0.00 0.02 0.84 0.86 0.68 0.10 0 . 1 2 0.14 @. 16 0.18 DRFIG COEF.

Figure 3-10 ( c ) Drag, Small S c a l e Figure 3-11 Effect of Canard St-rake 23, Configuration 401E-4, M = 1.20 (a) L i f t and P i t c h i n g Moment .

8 . 2 6.3 8.4 8 . 5 0 . S 0.7 8.3 8.9 D R Q G COEF.

Figure 3-11 (b) Drag, Large Scale Figure 3-12 Comparison 6 E Canard Strakes (ZU,, ZIB, 23) Configuration 40lF-5, M 0.80 (a) Lift and Pitching Moment 0 . 0 0.1 0 . 2 8 . 3 0.4 0 . 5 0 . 7 0 . 8 0.9 1 . 0 1 . 1 DRRG@%EF.

Figure 3-12 ( b ) Drag, Large Scale 4 . 9 ~ 0 . 8 6 9. QB 6 - 1 9 B , I ~ 0 . 1 ~ e. lc; 0.18 DPRG COEF.

Figure 3-12 ( c ) Drag, Small, Scale 8 5 30

QNGL :'$F R T f ~ C K . D?GREES*~

Figure 3-13 Comparison sf Canard Strakes (ZlA, ZlB, 23), Configuration 401F-5, M = 1.20 (a) L i f t and P i t c h i n g Moment 0 . 0 0 . 1 0 . 2 0.3 0 . Y 0.5 9.6 0 . 7 e.0 8.9 1 . 1 D R R G COEF.

Figure 3-13 (b) Drag, Large Scale 0 - 6 0 0 . 0 2 b bfl K\8 06 0 . 0 8 0.15 B . 12 0 . ? t i 0 - 16 8.18 @ DRRG CQEF.

F i g u r e 3-13 (c) Drag, Small S c a l e

z I-

;r LL?

Effect o f Leading Edge Flap D e f l e c t i o n w i t h Forebody Figure 3-14 Strake 24, Configuration 401F-5, M = 0.80 (a) Lift and Pitching Moment e. o 0 . 1 D.;? (1.3 0 . '4 ( 1 . 5 0.6 0.7 6.6 0 . 9 1 .B 1 . 1 DRRG CUEF.

Figure 3-14 ( b ) Drag, Large Scale Figure 3- 14 (c) Drag, Small Scale 8 . 8 8.1 8.2 8.3 8 . 4 8 . 5 0.7 0 . 8 8.8 1.0 1 . 1 DRRG"?OEF.

Figure 3-15 (b) Drag, Tkrge Scale SYM TEST RUlJ LEF TEF HT MOCH CONF

* 1932 437 0

0 0 0 . 8 0 OFF -----@---- 1932 Y 28 + 1 6 0 8 6.80 OFF --ffl-- 1932 573 15 0 0 0 . 8 B OFF 1932 448 25 0 B 0.80 OFF 8 . 0 0 0.02 0.04 0.06 0.18 0.12 B. 1 Y 0.16 @. 18 '-'BRRc COEF, Figure 3-15 ( c ) Drag, Small Scale I - LL?

+'* J Figure 3-16 Effect of Forebody Strake 24, Configuration 401F-5, LEF = 15*, M = 0.80 (a) Lift and P i t c h i n g Moment k'igure 3 - 1 6 (t)) Drag, Large S c a l e Figure 3-16 (c) Drag, Small Scale -5 8 5 1 0 25 38 . 1 8 . 2 0 . 8 ' 0 . 2 ' C 1 . 4 PITCH MOM. COEF.

WOLE OF R T ~ ~ C K . DZEBGREES

Figure 3-17 E f f e c ~ nF Forebod:? S t r a k e 24, C o n f i g u r a t i o n 40lF-5,

Z.EF - 2";'-?, M = 0 . 8 0

(a) L i f t and P i t c h i n g Mment I- LL?

' - a J Figure 3-17 (b) Drag, Large Scale 5 ze 16 ze 25 20 RNSCE OF RTTRCK, DEGREES

F i g u r e 3-18 Effecr o f Forebody - Strake Blending (24), Configuration

41)I-F-5, LEF O,M = (3.80 (a) Lift and Pitching lament 8.8 3. 1 8 . 2 8.3 63. I( 8.5 8 . 6 0.7 8.0 0.9 1.0 1 . 1 DRnG COEF.

Figure 3-18 ( b ) Drag, Large Scale 0.00 9 - 0 2 0 . 0 4 0.06 8 . 8 8 0.10 0.12 0 . 1 4 0.16 0.18 DRFlG COEF.

Figure 3-18 ( c ) Drag, Small Scale i 0 . 2 0 . 0 ' 1 -2 - B .Y PITCH MOH. COEF.

Figure 3-19 Effect of Forebody - S t r a k e Blending ( Z 4 ) , Configuration L;OlE'-5, M 1.20 (a) LiEt and pitching Moment -+I932 938 5 0 0 1.20 OFF -*--I832 Y72 0 0 0 1 - 2 0 ZY --83.- 1932 612 9 0 B 1.2R ZYR B. 0 0 - 1 0 . 2 0.3 8.q 8 . 5 0 . 7 8.e 8 . 9 1.8 1 . 1 DRRG@&EF.

F i g u r e 3-19 (b) Drag, Large Scale 1 " ?" ....... '. .. " .... .." ..... ".... 1 ....,..+ ,.,... ......

........... .,.. . . . . ..........-.. ........#... 1: t::: ....... :.. ..,..,, ,,,..,. 1 0

I . CI

.. . . . . . ............. % , * . . I . ,.., *.... .,... ....._. (. ....,.,., .,....

I.,-.,. .... ", .. ... .I." ..... ,+ .::..- .... ,: . . . . 1 . . , . .,.i I y

I

. .

.. ,.. ,...,. ................ ..., ............................... ". ............................... I.. ,.A. ..-..... ! .. ........., ..........

. .

.... : .: . ...... . ..: ; . . . i... .... . : . , . . . . . ............... .-.\. ....... ,~,~..~,.~. .................. 1 ........ ::I Q ..... ; ,. .............................. .....,..., ..... ..-..,.... ..... ..*.., .. .: .. ;.....*..I. ..: ..,.. 1 ..-.. ........ " ..........

,.., Q ..,.." ..-... " ...-........ ........................... " .-.... . , - . . , $ . i -... ..: ....- " .....?... -; ..... .;..- .-..-.. ....., ;,.; ...... ...,........,..

. . . . . . . . . . . . . .

1 . . J J . : 1 , I

I i 8 . - + c i 5 38 $0.4 t9.2 8 . 8 ' 8 . 2 -0.q R N G L E ~ ~ F R T ~ ~ C K , ~ ~ G R E E S ~ ~ P I T C H UOM. COEF.

.Figure 3-20 Effect of Forebody Strake Blending ( 2 4 ) , Configuration 401F-5, ZEF = lo0, M = 0.80 (a) Lift and P i t c h i n g -Moment 8.2 8.3 0.9 8.5 8.7 8.8 0 . 9 1.8 D R R G ~ C O E F .

F i g u r e 3-20 (b) Drag, Large Scale Figure 3-20 ( c ) Drag, Small Scale Figure 3-21 Effect of Forebody Strake 24 and 25, Configuration

~ o I F - ~ , LEE = 0, r! - 0.80

(a) L i f t and Pitching Momenr 0.1 (D. 2 0.3 0 . V B.5 8.7 B.8 0.9 f - 0 1 . 1 DRRG'~!OEF.

Figure 3-21 (b) Brag, Large Scale ill ri m V?

J a W" o m : . . .

. . . . . . .

. .

. . .

i;. . . . . . : . . ..

.....

B 5 10 15 20 25 RNGLE OF R T T R C K , DEGREES F i g u r e 3-21 ( d ) Increments 34 1 6 . 3 6.4 8 . 5 0.7 0.8 B.Q 1 .G DRRG*?OEF.

Figure 3-22 (S) Drag, Large Scale 0 . a0 0. C 1 2 6.811 0.08 0 . I0 9.12 0 . t 4 0.16 (2. I t 3 DRRG COEF.

Figure 3-22 ( c ) Drag, Small StraLe 5 10 15 28 RNGL, OF R T T R C K , DEGREE;' Figure 3-22 ( d ) Increments 34 5 F i ~ t ~ r e 3-23 E f f e c c of Fuzebody S t r a k e s 24 and 2 5 , Configuration 401F-5,

LEF = l o o , 14 = 0. G O

(a) L i f t and P i t c h i n g llornent 9 . 0 8 . 1 8- 2 8 . 3 0.U 8 . 5 6.7 0.8 6.9 1 -6 1 . 1 D R A G ~ $ O E F .

F i g u r e 3-23 (b) Drag, L a r g e S c a l e 0 . 0 0 0 . 0 2 0 . 0 8 0 . 1 0 0 . 1 2 0 . 1 4 0. 16 @ . 18 DRRG COEF.

Figure 3 - 2 3 (c) Drag, Small Scale ORIGINAL PAGE I S OF POOR QUALITY -..--- 1032 Y99 10 0 B 0.80 '15 *** BRSELINE RUN (I" t - & J W D

s ~ N G L $ * O F R T ~ S R C K , DEGREE? 20

Figure 3-23 (d) Increments I- LL?

'-+w J Figure 3 - 2 4 Effect of Delta Planform Forebody Strakes (27-210) Configuration 785, LEF 0, M 0.80 (a) I,if t and P i t c h i n g Moment 9 . 8 8.1 0.2' 8.3 0 . 5 8.6 8.7 8 . 8 0.9 DRFIG COEF.

Figure 3-24 (b) Drag, Large Scale SYH TEST RUN LEF TEF HT MRCH CONFIG 1831 163 0 0 0 0.80 OFF 0,80 27

--a-- 1931 183 0 0 0 0.8@ Z 8

196 0 0 0 1831 188 0 0 0 0.80 210 0.86 0.08 0.10 0 . 1 2 0.1L' 0.16 0 . 1 8 ORQG COEF.

Figure 3 - 2 4 ( c ) Drag, Small S c s l e ORIGINAL PAGE If OF POOR QUALITY J m w- oe: war 1931 1630 B B 8 . 8 6 OFF

- 1931 171 8 0 O Q . 6 0 L7

f ' !

Q B 5 15 90

RNGLE''OF R T T R C K , FEBEGREE~'

Figure 3-24 ( d ) Indrements Figure 3-25 (b) Drag, Large Scale ---ff-- 1031 16.1 0 0 0 1.2Q OFF 168 0 0 0 1.20 Z8 -......- + .... ".. 193 1 199 0 0 0 1.20 Z 9

-.---*---- 193 1 187 (1 0 0

1.28 Z 1 8 8.08 0.10 8 . 1 2 8.14 0. L 6 0. I8 DRFIG COEF.

Figure 3-25 ( c ) Drag, Small Scale Figure 3-26 Effect o f Delta Planform Forebody Strakes (27, ZIO) Configuration 385, LEP = 5", tl = 0.80 (a) Lift and Pi tchin2 Moment 0.2 0 . 3 0.4 8 . 5 0.8 0 . 7 0.8 8.9 1.9 1 . 1 ORRG COEF.

Figure 3-26 ( b ) Drag, Large Scale ORIGINAL PAGE IS Olp POOR QUALITY . , .:.,; +.i, .{ , ; , I . ,;.; ,; . ,, .

i, :~i 0" ""' " "'"" " ' ., . , ; , ; '* .. ,., i * 4 i . , . . , . ,A, .!. .?..+).

..... l . . l . i . . r ....- i . .... . ; . .,.. . .

. .

- ..,. b,- '.. ..,... ,,, -..; ,*,.

+ ; r ..a,! i .i .h.i.,. i. ..I... ! I . .: ;.+i3.

,;,., 1.5 .;.; .,: . * d . , . , , ...,.a ...

. ..:.ir.,!, .;+)..;,..i.;.:.!. <.,.: 7 : i.; i . j ? : ,i .; ,. . , ; ; : ::I;:/ ,r:. LL; :,? ,,12 ; ,;:, .-.!:j,.

.,,.!.? ! .., ? +,, . ;.?.3.; .;..!..!..!

. .

7, i,: .!. ,,!. , ! i.,." TS., ; ., ...... ,-.". ....... " ... .-.* ............

PEF HT MF,CII COFIFIG 1 . : : : : ,:;*: : , ; :;;,:; j , : , ,?$:$:?

,,/..I $ 4 .... l..tv.t. .,.. , . $ . .... ;:.is. 1730 95 5 Q O C , S C OFF ..!.,' : '. .. > '.:, i.:.!.i . ; A .... 2.. . . B i 2 B . b 2 i'7 Figure 3-26 ( d ) Increments (27,210), Eigure 3-27 Effect oE Delta Planform Forebody S t r a k e s C o n f i g u r a t i o n 785, LEE = i 5 O , I? IL 0.80 (a) LiEt and P i t c h i n g Moment -6 8 5 38 t8.4 + 0 . 2 - 8 , :I RNGLEI'OF AT; RCK , ~ ~ G R E E S ~ ~ P I T C ~ @ N O M ?C?OEF.

E f f e c t : o f H o r i z o n t a l T a i l Deflecti-on with Forebody S t r a k e 27, F i g u r e 3-28 C o n f i g u r a t i o n 785, 1 1 = 0.80 ( a ) L i f t and P i t c h i n g iloment 8.8 £3.1 B . 2 B , 3 B - Y 8.5 0 . 7 C. 8 B . 0 1.8 1.1 D R R G ~ ~ O E F .

F i g u r e 3-28 (b) Drag, Large Scale 11331 229 IS 8 OFF 6.86 1031 2!8 15 B 0 F i g u r e 3-21; ( c ) Drag, Small Scale I- LL?

Figure 3-29 Effect of Horizontal Tail Deflection Without a Strake, Configuration 785, M = 0.80 (a) L i f t and Pitching Moment

--*--- 1730 89 15 9 0 9.80 OFF

1730 46 15 0 -Z0 B.80 OFF F i g u r e 3 - 2 9 (b) Drag, Large Scale

'*

Figure 3-24 (c) Drag, Small. S c z l c -5 5 28 25 t6.4 + 8 . 2 B . 0 - 0 . 2 - -(I 14 P I T C H MOR. CUEF.

QNGLE"OF A T GCK. DEGREES

F i g u r e 3 - 3 0 Effect: o f S t r a k e 27 on H o r i z o n t a l T a i l E f f e c t i v e n e s s , C o n f i g u r a t i o n 7 8 5 , If = 0-80 (a) Lift a n d P i t c h i n g I!oriient B . 3 8 .Y 9 - 5 8.7 H-Z 8.e L , % I I DRFIF ' & E F .

(b) mag, Large Scale SYM TEST RUN LEF TEF HT MRCil CONFIG em* 1730 46 is o -20 a,scr o ~ r : 1931 231 15 0 -200,5v? 2:: 0 5

R N G L E ~ O O F A T ~ C K , FEPEOREE~'

Figure 3-30 (d) Increments I- LL?

'-'% J 5 10 15 29 25 3 0 UNGLE O F R T T R C F , DEGREES Figure 3-31 Effect o f Leading E d g e Flap Deflection Wirh Strake 27, C o n f i g u r a t i o n 785, t+ 0,88 (a) Lift a n d P i t c h i n g Moment Ffgure 3-31 (b) Drag, Large Scale I- LL?

' - ' e -I Figure 3-32 E f f e c t o f Forebody Strake 27, Configuration 7 8 6 , LEF = 0. M = 0.80 (a) L i f t and Pitching Moment Figure 3-32 ( b ) Drag, Large Scale 04 0 . 0 6 0 08 0.10 0.12 0.14 8.16 0.18 DRQG CDEF.

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RNGLE'$F R T %CK , ~ ~ G R E E S ~ ' Figure 3-33 Effect of Forebody Strake 2 7 , Configuration 786, M = 1.20 (a) L i f t and Pitching Moment 0.8 * 0.1 8.3 O.Y 8.5 0.7 e.e e-9 1.8 I I D R A G @ ? O E F .

Figure 3-33 (b) Drag, Large Scale b . GB @,BE? U,. l% F. i 2 %, 1% b . k G DREG COEF, Figure 3-33 ( c ) Drag, Small Scale 6 . 0 8.1 0.2, 0.3 0 . Y 0 . 5 0 . 6 0.7 0 . 8 0.3 1 .@ 1 . 1 DRQG COEF.

Figure 3-34 (b) Drag, Large Scale 6 , 0 2 0 . bfl b . 0 I @ , I 0 cj. 12 D R N G COEF + Figuxe 3-34 (c) Drag, S m a l l seal^ Figure 3-35 E f f e c t of Ogee Planform Forebody Strakea (214, 216-Z18), , Cortfiguration 48fF-5, M = 0.80 (a) L i f t and P i t c h i n g Moment 8.8 0 . I 0 . Z 8.3 0 . 1 ) 8.9 0.6 6.7 B . 8 8 . 9 1 . O f l DRQG COEF.

F i g u r e 3 - 3 5 ( b ) Drag, Large Scale 8 . 0 0 0.82 0.04 . 0.06 0.08 0.10 0.12 81.14 8.16 0.18 DRRG COEF.

Figure 3-35 (c) Drag, Small Scale . , . . " I * , .

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Figure 3-36 Effect .of Forebody Chines (220,221) and Canard Strake Z l A , Configuration 401F-10A, LEF = 0, M = 0.80 (a) L3-f t and Pitching Moment 0.1 8.2 0 . 3 0.4 0 . 5 8 . 6 0 . 7 0 . 8 8.9 l . @ 1 . 1 D H R G COEF.

F i g u r e 3 - 3 6 (b) Drag, Large S c a l e Figure 3-36 (c) Drag, S m a l l Scale Figure 3-37 E f f e c t o f Forebody c h i n e s ( 2 2 0 , 2 2 1 ) a n d Canard S t r a k e ZlA, C o n f i g u r a t i o n 401F-10A, M = 1.20 (a) L i f t and Pitching Moment -2131 100 B 0 0 1.28 OFF ---tE)--- 2131 53 8 8 0 1.20 228 --Eff-- 2131 71 8 8 0 1.20 221 Figure 3-37 (b) Drag, Large Scale

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I- LL?

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-.#-- 2131 05 10 8 9 8 . 8 0 ZIR Figure 3-38 Effect of Forebody Chines (Z20,Z21) and Canard Strake Z l A , Configuration 40LF-IOA, L E F = ~ O O ,M = 0.80 (a) L i f t and P i t c h i n g Moment Figure 3-38 ( c ) Drag, Small Scale Figure 3-39 Effect of Forebody Chines (Z20,221), Configuration 40lF-10A, LEF = 25', M = 0.80 ( a ) L i f t and Pitching Moment O.B 8.2 8 . 3 9 . Y 9 - 5 0.0 0.7 9-53 B.B 1.9 1.1 DRGG COEF.

Figure 3-39 (b) Drag, Targe Scale I 8 . 8 8 0 . 8 2 0 . 0 Y 0 . 0 6 0.0- 0 . 1 0 0 . 1 2 8 . 14 8 . 1 6 0 . 1 8 DRFlG COEF.

Figure 3-39 ( c ) Drag, Small S c a l e Figure 3-40 Eomparison of Forebody Strake 222 with Canard Strake Z l A , Configuration 401F-5, LEF = 0 , M = 0.86, (a) L i f t and Pitching Moment 0.00 0.02 0.04 0.06 0.08 8.10 0.12 0.1'4 8.16 0.18 DRFlG COEF.

Figure 3-40 (c) Drag, Small Scale Figure 3-41 (b) Drag, Large Scale h M

2s

Figure 3-42 Effect of Forebody Strake Shape (224-227), Configuration 401F-10A, EEF 0 , M 0.80 ( a ) L i f t and Pitching Moment Figure 3-42 (b) Drag, Large S c a l e SYN TEST RUN LEF T E F HT FlRCil C:CII'~FICI *-* 2131 98 0 0 0 0. E;: OFF

- 2131 1 8 2 8

0 0 @ . t i c , ZZLt -5 0 . 5 15 20 RNGLE"OF RTTFICK, D E G R E E : ' F i g u r e 3 - 4 2 ( d ) Increments Figure 3 - 4 3 Effect of Forebody Strake Shape ( 2 2 4 - Z 2 6 ) , Configuration 4OLF-lOA, E F = 0 , M 0.90 (a) L i f t and P i t c h i n g Moment 8.1 8.2 9.3 8 . 4 8.5 8.7 8.2 6 . 9 I - a I . i DRRG'~%EF.

Figure 3-43 (b) Drag, large Scale 0.00 0.02 12-84 0.06 0.08 0.10 0.12 0.14 0.16 0.18 DRQG C O E F .

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a t - d m w- o m : Figure 3-43 ( d ) Ixicrements 4 15 Figure 3 - 4 4 Effect of Forebody Strake Shape ( 2 2 4 - Z 2 7 ) , Configuration 40lF-lOA, LEF = lo0, M = 0 . 8 0 (a) L i f t and Pitching Moment 9 . 2 0 . 3 e,'f 8+S 8.7 0. B 0.9 1 .@ 1 . 1 D R R G ~ ~ O E F .

Figure 3-44 (b) Drag,, Large Scale 0.00 0.02 0.04 -0.06 0.08 r d . 10 0.12 8 . 1 4 0.16 0.18 DRQG COEF.

Figure 3-44 ( c ) Drag, Small Scale a- t-d J 5 10 1 S RNCLE OF A T T R C K , ~ ? E G R E E ~ ~ F i g u r e 3-44 ( d ) Increaents I- L L ?

W B J Figure 3-45 Effect of Forebody Strake Shape ( 2 2 4 - Z 2 6 ) , Configuration

401F-10A, LEF = lo0, M = 0 . 9 0

(a) L i f t and Pitching Moment 8.2 6.3 8.4 0 . 5 8.6 0 . 7 0 . 8 0 . B 1.0 DRFlG COEF.

Figure 3-45 ( b ) Drag, Large Scale 0.00 0 . 0 2 0 . 0 8 0 . !@ 0.12 8.14 0.16 0.18 DRQG COEF.

Fi ;?.me 3-45 ( c ) Drag, Small Scale -- s q u a m a ~ x ~ ( p ) ~ 4 j - g a z n a ~ d S X I U ~ ~ ~ ' ~ I ~ U . L L U do 3 i o ~ t ~ Si3 02 s I 8 1 S

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Figure 3 - 4 6 Effect of Forebody Strake Shape (224-227), configuration 401F-10A, LEF =: 25', M = 0.80 (a) Lift and Pitching Moment 8.1 0.3 0 . 0 0 . 5 8 . 7 8.8 8.9 1.0 1 . 1 DRRG@~!OEF.

Figure 3L46 (b) Drag, Large Scale 0; o m : La- t-i -I W n

0 . 5 RNGLE"OF RT%CI(, FEGREE?

Figure 3-46 ( d ) Increments

Figure 3-47 Effect of oreb bod^ Strake Shape (228-Z31), Configuratian

49L.F-16, LEF = 0 , M 8.80 (a) L . i f t and p i t c h i n g Moment 0.1 8.2 8.3 O.S 8.5 0 . 7 B . 8 8.8 1.8 1 . 1 DRRG@.~"OEF.

t Figure 3-47 (b) Drag, Large Scale 0.00 0 . 0 2 0.84 0.06 0.08 0.10 0.12 0.14 0.16 8.18 DRRG COEF.

Figure 3-47 ( c ) Drag, Small Scale f ' ?

0 s 1 e 15 28 t s RNGLE OF PITTRCK, DEGREES Figure 3-47 ( d ) Increments Figure 3-48 Effect of Forebody Strake Shape (228-Z31), Configuration

LEF = lo0, M = 0.80

601F-16, (a) Lift and Pitching Moment

----e---- 2230 366

10 0 0 8 . 8 0 7128 --ffl---223B 373 10 0 0 0 . 8 0 230

-.--*-- 2230 383

10 0 0 0.89 229 Figure 3-48 ( c ) Drag, Small Scale SYM TEST RUN LEF TEF HT M A C H C O N F l t i m*a 2230 3 5 Z 1 0 0 0 0.83 Z2l 2230 366 18 0 0 0 . 5 0 Z2a B 5

RNGLE'@OF R T ~ F I C K , FEGREE?

Figure 3-48 ( d ) Increments Figure 3-49 Effect of Fsrebcdy Strake Shape (228-2311, Configuration 401F-16, LEF -25O, M = 0.80 (a) L i f t and P i t c h t n g Moment @ - 2 0.3 6 . 0 . 5 0.6 0 . 7 8.8 8.9 DRRG COEF.

Figure 3 - 4 9 (b) Drag, Large Scale Figure 3-49 ( c ) Drag, Small Scale SYM TEST RUN LEF TEF HT MRC1-i tOlJFl G *** 2236 360 25 B 0 O. f2.d 251 2230 363 25 0 (3 0.80 Z2G Figure 3-49 ( d ) Increments Figure 3-50 Effect of Forebody Strakes 229 and 232, Configuration

40LF-16, LEF - 10°, M = 0.80

(a) L i f t and Pitching Wrnent I 0 . 0 0 0 . 8 2 0.04 06 0 . 0 8 8.10 0.12 0 . 114 0.16 0.18 DRQG COEF.

Figure 3-50 ( c ) Drag, S m a l l ScsJ-e Figure 3-51 Effect of Forebod Strakes 229 and 232, Configuration 401F-16, LEF = 25', M = 0.80 (a) Lift and Pitching Moment 8.8 8.1 8 . 2 8.3 8.4 6.5 8.7 6 . 8 9.9 1 . B 1 . 1 D R A F ~ % E F .

Figure 3-51 (b) Drag, Large Scale 8 5

ANGLE'@OF RT%CK, FEGREE~'

Figure 3-51 ( d ) Increments 8.8 8.1 8.2 6.3 8.4 0 . 5 0.6 8 . 7 8 . 8 e.9 1.0 1 . 1 DRRG COEF.

Figure 3-52 (b) Drag, Large Scale ORIGINAL PAGE 1 " OF POOR Q U A L ~ SYM TEST RUN LEF TEF HT MRCtI C O t J F I G 2330 590 0 8 0 0.80 Z5; w* BRSELINE RUN . . .

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RNGLE OF R T T R C K , WGREE;'

Figure 3-52 ( d ) Increments 4 5 3 Figure 3-53 Effect of Forebody StraYes 231 and 233, Configuration 401-16 LEF = lo0 M = 0.80

( a ) ~ i l t and pitching Moment

8.8 8.1 6.2 8 . 3 8.9 8.5 e.7 8.8 8. f3 1.8 1.1 DRRG@$OEF.

Figure 3-53 (b) Drag, Large Scale Figure 3-53 ( c ) Drag, Small Scale Figure 3-53 ( d l Xt~cwements

-- 4 57

0.1 8-2 0 . Y 8 . 5 8 - 6 0.7 8.8 8.9 1 .B DRFiG CUEF.

F i g u r e 3-54 (b) Drag, Large Scale

0 . 0 2 8 . 0 4 9 - 9 6 @.@a 0.10 8.12 8 . 1 4 0.16 0.18

DRRG COEF.

Figure 3 - 5 4 ( c ) Drag, Small Scale Figure 3-55 Effect o f Forebody Strakes 233 and 250, Configuration 40lP-16E, M 0.60 (a) Lift and Picching Moment 8.80 0 . 0 8 0.10 0.12 0 . '14 8.16 0.18 DRRG C O E F .

Figure 3-55 ( c ) Drag, Small Scale Figure 3-56 Effect of Forebody Strakes 233 and Z50, configuration

402F-16E, LEF 0, M - 0.80

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b

Figurc 3-56 (c) Drag, Small Scale I -

* LL?

m 00 J Effect of Forebody Strakea 233 and 250, Configuration Figure' 3-57 401F-16E, M = 0.90 (a) Lift and Pitching Moment 0-0 B, I a +z 9 . 3 8.4 e -5 1 . 7 e , ~ a.a X-e 1 . I ORRG'ZOEF, Figure 3-57 (b) Drag, Urge Scale 0.00 0.08 0.10 0.12 0 . LY 0.16 0.18 DRFlG COEF.

"'" \ & " r e 3-57 . (c) Drag, Small Scale P i p r e 3-58 E f f e c f : of F~r~re'mdy Seraks 233 and 250, &nEiguratZon 401~-LSE~ li 2L 2.20 <a) L t Z t and P%f=ching 15amen.t: I- LL?

Hal -1 8.2 8.3 8.4 9.5 0.7 6 . 8 8.8 1.8 1 . 1 DRRG'~!OEF.

Figure 3-58 (b) Drag, Large S c a l e o f : Figure 3-58 (c) Drag, .Small Scale E f f e c t of Forebody Strakes 233 and 250, Configuration Figure 3-59 401F-16E, LEF 2 5 O , M 0.80 (a) L f f t and P i t c h i n g Mcment 0.8 8.1 8.2 8.3 8.9 8.5 8.7 0.8 8.9 1.8 1 . I D R E I G ~ ~ O E F .

Fiwte 3-59 (b) Drag, Tsrge Scale (e) Drag, S m a l l Scale l?i&re 3-59 Figure 3-60 E f f e c t cf Forebody Strake Shape ( ~ 3 3 , 2 4 8 , -Z50), Congig- u r a t i o n 401F-16E, M = 0.90 .(a) L i f t and P i t c h i n g Moment 0.00 8.02 0.0Y 0.06 0.08 0.10 8 . 1 2 0.14 0.16 0.18 DRQG COEF.

Figure 3-60 ( c ) Drag, Small Scale Figure 3-61 Effect of Foxebodg Strake Shape (263-Z66,271), YF-16+30.5 . S t r e t c h , M = 0 . 8 0 (a) L i f t and P i t c h i n g Moment , Figure 3-61 ( c ) Drag, S m a l l Scale

ORIGINAL PAGE B

OF POOR Q U A L ~

- 5 B 5 R N G L E ~ ~ O F A T % C K , KEGREE?

Figure 3-61 (d) Increments -5 9 5 38 t9.Y t8.2 -@.2 -0.4 R N G L E ~ ~ F ~ E c K , G ~ G R E E S ~ ' P I T & ' M O ~ . EOEF .

Figure 3-62 E f f e c t of Forebody Strake Shape (263-Z66,271), YE.-16+30,5 S t r e t c h , LEF = 0, M = 0.90 (a) ~ i f t and Pitching Moment 8.8 8.1 8.2 8.3 8 . Y 8.5 8.7 8.8 8.8 1.8 1 . 1 DRRG'$OEF.

Figure 3-62 (b) Drag, Large Scale 8.80 0 . 0 2 8 . 8 4 0 . 0 6 0 . 0 8 0.18 8.12 0 . 1 4 8.. 16 0.18 DRFlG COEF.

Figure 3-62 ( c ) Drag, Small Scale ORIGINAL PAGE IS OF POOR QUALITY -- --. - Figure 3-62 (d) Increments 0.8 9.1 8.2 8.3 O . Y 0.5 8 . 7 9.8 63.8 1.0 1 . 1 D R A G ~ $ O E F .

Figure 3-63 (b) Drag, Z a q e Scale 0.08 8.02 0.04 0.06 0.08 0.10 0.12 8.14 8.16 0.18 DRRG COEF.

Figure 3-63 ( c ] Drag, Small Scale LI

i

-6 . 0 5 28 25 30 A N G L E ~ ~ O F R T ? ~ R C K . D E G R E E S Figure 3-63 (d) Increments Figure 3-64 Effect of Forebod Strake Shape (263-266,271), YF-16+ 30.5

B

: Stretch, LEF = 25 , E.r_ = 0.90 (a) L i f t and Bitching Moment 6.8 8.1 8.2 0 . 3 8.9 8 . 5 0 . 6 8 . 7 8.0 8.8 S .0 1 . 1 DRFlG COEF.

FLgure 3-64 (b) Drag, Large Scale 0.00 0.02 0.04 0.06 0.88 0.18 0.12 0 - 14 0.16 0.18 DRRG COEF.

FPgure 3-64 ( c ) Drag, Small Scale E f f e c t of Forebody Strake Shape ( 2 6 3 , 2 6 4 , 2 8 7 , 2 8 8 ) YF-16+ Figure 3 - 6 5 30.5 Stretch, M = 1 . 6 0 (a) L i f t and P i t c h i n g Moment

f

. .

L;"!

W" I- LL'?

'-43 A -t d ?

B ?

8.8 @. 1 8.2 8.3 0 . Y 8.5 8.7 8.8 8.8 1.6 1 . I DRRG"~!OEF.

Figure 3-65 (b) Drag, Large Scale SYH TEST RUN LEF TEF HT HnCH CONFIG 0 1.68 263 A 3750 18 0 0 Z6Y 0 3750 I S 0 0 0 1.60 3750 44 0 0 0 1.60 288 0 . 8 0 0.02 0.04 0.86 0.08 0,10 0.12 0.14 0.16 0.18 DRQG COEF.

Figure 3-65 ( c ) Drag, Small Scale I;" w- I- LL?

H e -1

Figure 3-66 Effect o f Forebody Strake Shape (263,264,287-288) YF-16 +

5 0 . 5 '~tretch, E1 = 2 . 0 0 (a) L i f t and Pitching Moment 8.8 8.1 0.2 8.3 0.9 9.5 8.7 8.8 8.9 1.0 1 . 1 D R A G ~ ~ O E F .

Figure 3-66 (b) Drag, Large Scale 9.00 0.02 8 . 0 Y 0.06 8 . 0 8 0.10 8. 12 0 . 1 4 8.16 ' 0.18 DRRG COEF.

Figure 3-66 (c) Drag, Small Scale I- LL?

' - ' a J Effect o f Nose Strakes 273' and 274, YF-16+,30.5 Stretch, Figure 3-67 M = 0.80 (a) L i f t and Pitchfng Moment ............. 4 s . . . . i ............ ,,!.. ..~..,..,..,. ....... i..

. .

....... ... ...... ... '.".'...!'. .*.) .,." "4.. ""' ..-. "..*'.

.I.... . . . . . . . .......................... .,is,, ,,i..i ,.,*.... *..

.. i..;...;.. .............. I...,. . . . a ..... a..* ............ i .

... ... .......

8. 80 0.02 8.04 8.06 9.88 8.10 0.12 8.14 0.16 0.18 DRRG COEF.

Figure 3-67 ( c ) Drag, Small Scale t 0 . 2 -8.2 -0.4 P I T & ~ M O M . COEF .

Effect of Nose Strakes 273 and 274, YF-16+30.5 Stretch, Figure 3-68 Ea = 0.90 (a) L i f t and Pitching Moment 8.2 8.3 0 . g 0 . 5 8.7 0 . 8 0 . 9 . 1.8 1 . 1 D R R G ~ $ O E F .

Ffgure 3-68 (b) Drag, Large Scale 0.00 8.02 0.84 0.06 0.08 C?. 10 0.12 B. 1Y 8.16 0.18 DRQG COEF. I Figure 3-68 (c) Drag, Small Scale 4e.u ' +@.a -8.2 -0.v P I T<H@MDM. COEF.

Effect of Nose Strakes 273 and 274, YF-163-30.5 Stretch, ~ i g u r e 3-69 M = 1.20 (a) L i f t and Pitching El0a@3ne Figure 3-69 (c) Drag, Small Scale '3303 'WOW H311d h'5- Z - B - 0 . 8 e a O + h - e l 6 S h l BE9E -4&- B IhI OEQE -P- I 8 . 0 0 8.82 8.011 0 . 0 6 0 . 0 8 0.18 B. I 2 0 . 1 4 0.16 0 . : 8 DRFSG COEF.

Figure 3-70 (c) Brag, Small Scale ORIGINAL PAGE IS OF POOR QUALITY -5 8 5

RNGLE'OOF R T ~ R C K , FEBEGREE?

Figuee 3-70 ( d ) Increments E f f e c t of Forebody Strake Size (272,275,280) YF-IS+ Figure 3-71 30.5 Stretch LEF = 0 , M = 0.90 ( a ) L i f t and P i t c h i n g Moment I- LL?

-8 -I Figure 3-71 (b) Drag, Large Scale In t - ' m 8.00 0.02 8 . 0 4 0.06 @ , 88 8.18 0.12 8 . 1 4 0.16 0.18 DRFlG COEF.

Figure 3-72 (c) Drag, Small Scale ORIGm.At PAGE IS POOR Q U - 0 5

R N G L E ~ ~ O F R T K ~ C K , W G R E E ~

I Figure 3-71 ( d ) Increments 8 5 3 0 t 0 . q t8.2 -0.2 -0.': P I T C ~ ~ M O M . COEF .

A N G L E ~ ~ F R T ~ ~ C K , ~ ~ G R E E S ~ ~ Figure 3-72 Ef feet of Forebody Strake S i z e (272,275,280) YF-16+ 30.5 Stretch, K = 1.20 (a) L i f t a i d Pitching Moment I 8.8 8 . 1 8.2 8.3 8.4 8 . 5 8 - 7 8.8 8.9 1 - 8 1 . 1 DRRG e C o ~ ~ .

Figure 3-72 (b) Drag, Urge Scale 8 . 0 0 8 . 0 2 0.04 0.06 0 =08 0.10 0.12 8 . 1 4 0.16 0.18 DRFIG COFF.

~ i g u r e 3-72 ( c ) Drag, S m a l l Scale F i g u r e 3-72 (d) Increments Effect of Forebodv Strake Size (272,275,280), YF-16+30,5 Figure 3-73 Stretch, LEF = 25', EI = 0.90 (a) L i f t and P i t c h f n g Moment Figure 3-7 3 (b) Drag, Large Scale (c) Drag, Small. Scale Figure 3-7 3 ORIGINAL PAGE IS OF POOR QUALITY (d) Increments Figure 3 - 7 3 Effect of Canard Strakes Z1D and 281, YF-16M0.5 figure 3-74 Stretch, M = 0 . 8 0 (a) Lift and Pitching Moment I- LL" J B . 8 8.1 8.2 8.3 e.9 8 . 5 8.7 8.8 8.9 1 - 8 1 . 1 DRRG~POEF.

Figure 3-74 ($3 Drag, Large Scale 8.80 0 . 0 2 0.04 0 . 0 6 0 . 0 8 0.10 8.12 0 . 1 4 8-16 0.18 DRFlG COEF.

Figure 3-74 (c) Drag, Small Scale I- LL?

' - ' B J E f f e c t of Canard Strakes Z1D and Z81, YP-16+30.5 ~ i b r e 3-75 . Stretch, LEF = 0,. M = 0 . 9 0 (a) L i f t and Pitching Moment ' 8.3 0.4 6 . 5 8.7 8.8 0.9 1 .8 1 . 1 DRQG'?OEF.

-Figure 3-75 (b) Drag, Large Scale 0.00 0.02 0.04 0.06 0.08 0.10 0. ;2 0 . 1 4 B . 16 0.18 DRGG COEF.

Figure 3-75 ( c ) Drag, Small Scale Effect of Canard Strakes Z 1 D and 281, YF-164-30.5 Figure 3-76 Stretch, M = 1.20 (a) L i f t and P i t c h i n g Moment 8.8 8.1 8.2 8.4 8 = 9 8.5 8.7 6.8 8.9 1 .B 1 . 1 D R R G ~ ~ O E F .

Figure 3-76 (b) Drag, h r g e Scale 8 . 0 8 0.02 0.04 0.06 0 . 0 8 0.10 0.12 0 . I Y 0.16 0.18 / DRRG COEF.

Figure 3-76 ( c ) Drag, S m a l l Scale SYH TEST RUN LEF TEF HT WRCH CONFIG -&- 3638 118 25 B 8 6.98 263 -&- 3630 26'1 25 0 0 ff .9Q +t81 ~ i b r e 3-77 Effect of Canard Strakes Z1D and 281, YF-16i-30.5 Stretch, L E F ~ ~ O , M = 0.90 (a) LfEt and Pitching Moment SYH TEST RUII LEF TEF HT W G H 118 2 . 5 B 8 e-a@

* 3628

e 0 0 . 9 s --++3=0 115 25 @.L38 --B--. 3638 264 25 B B Figure 3-77 [c) Drag, Small Scale -3 t -6 B s 18 1s JB i e .LI to.;? -8.2 0e.9 PIT&'MOM. COEF .

ANGLE OF RTTRCK, E?GREES~' Figure 3-78 E f f e c t oE Nose Strake 2100, F-16, M = 0.90 (a) L i f t and P f t c h i n g Moment 'f 0 . 0 8.1 8.2 8 . 3 8.4 6 . 5 8.6 0.7 0 . 0 8.9 1.8 DRQG COEF.

Figure 3-78 (b) Drag, Large Scale 0 . 0 8 8-10 0.12 8 . 1 4 0.16 0.18 0 . 0 0 DEFIG COEF.

'." % - 0 6

Figure 3-78 ( c ) Drag, Small Scale t0.2 0 . 8 -0.2 - 0 . 1 1 -S 0 s 38 i 8 . v PITCH MOM. COEF.

ANGLE'^ R T ~ B C K , ~ ~ G R E E S ~ ~

Figure 3 - 7 9 Effect of Forebody Strake Shape (Z103,Z108), F-16, M = 0.90 (a) Lift aad Pitching Moment 0 . 0 0 0 . 0 2 - % \ -06 8.08 0.10 0.12 0 . 1 4 0.16 0.18 DRRG COEF.

%\ 3.

Figure 3-79 ( c ) Drag, Small Scale L'!

L o I-

LL?

-&I Figure 3-80 Effect of Forebody Strake Shape (Z103,ZlO8), F - 1 6 , M = 1.20 (a) L i f t and Pitching Moment I- LL?

'+a J Figure 3-80 (b) Drag, Large Scale Figure 3-80 (c) Drag, Small Scale I- LL?

-B A Effect of ?orebody S trake Forvard Extent (2103,2109), F-16, ~ i g u r e 3-81 M = 0.90 {a) T J f t and Xttcking Moment 0 . 0 0 0 . 0 6 0 . 0 8 0.10 0.12 0 . 1 4 0.16 C?. l b DRRG COEF.

\

Figure 3-81 ( c ) Drag, Small Scale SYM TEST RUN LEF TEF HT HRCI.1 CDNFIG Figure 3-81 (d) -- -- ... Increments .

FINGLE OF RTTRCK, DEGREES P,ITCH M O M . COEF.

E f f a c t o f Forebody S trake Forward Extend (Z103 ,A109), F-16, Figure 3-82 M = 1.20 (a) L i f t and pitching Moment 8.8 0 . I 8.2 8 . 3 e.81 0.5 8.6 8.7 0.8 B . B 1 . 0 3 . 1 DRFlG COEF.

Figure 3-82 ( b ) Drag, Large Scale Figure 3-82 (c) Drag, S m a l l Scale SYM TEST RUN LEF TEF HT t1RCtl CONFlB

- VQSO 69 1$ i! 8 1,EO Z109

a ' : U r n

e Is RNGL&@OF RTYRCK, ?E:EGREE~'

Figure 13-82 (d) Incmments 4- * 4 . TRANSONIC S I D E S L I P DATA d , , e - 1639 320 25 Y B 17.8 B , 8 0 OFF *.4@.

l6SQ 294 2s 4 O i S , 6 U . 8 B E l Figure 4 - 1 Effect of Canard Strake Z1, Configura- tion 401F-2 w i t h Ywin Vertical Tails M = 0.80

(a) Force -.&* -,. . and Moments . . . -...z....a--..s a - . 1 6 '

-, Q) ' I

-1s - 1 R -5 o 5 l a a s 20

0NGL.E OF SIDESLIP, DEGREES Figure 4 - 1 (b) Force and Moments, a = 27' I

-15 -18 - 5 RNGLE OOF SIDESLIP, ' ~ E G R E ~ ; ao

Figure 4 - 2 E f f e c t of Canard and Strake Z l A , Config- uration 401F-2 w i t h 7.5' W i n Vertical Tails, M m 0 . 8 0 ORIGINAL PAGE 1 5 POOIk QUAlJ'rY Figure 4-3 Effect o f Canard Strak? Z U , Configura- t$on 401F-2,with 7.5' -in Vertical Tails, M = 1.20 -1s -18 - 5 20

R N G L E BOF SIDESLIP , 'ODEORE&

Figure 4-4 Effect of Canard Strake Z I A , Configura- t i o n 401F-2 With 15' Twta V e r t i c a l

T a i l s , M - 1.20

(a) Force and Moments, a ! = O0 , - * . - . . h - - . ~ - .

S I D E F O R C E ROLLING MOMENT Y ~ W I N G MOMENT -8.69 -8.Y9 -9.29 B.90 8.28 - B . l @ -8.85 8.98 -0.38 -8.85 9.88 8.85 0. 10 QO Q zL" H'?

-Ie J' Em " Figure 4-4 (c) Farce and Moments, a = 20' . . - .- . . .. . ' ORIGINAL PAGE IS OF POOR QUALITY

- 15 -1, -5 28

RNGLE BOF S I D ~ S L I P , "DEGRE&

Figure 4-5 Effect o f Canard Strake Z l A , Configura- tion 401F-2 With l S O Twin Vertical T a i l s , LEF = 25', M = 0.80 (a) Force and Moments, = 15' =9 B s \ a 1% RNOLE OF CIZPESLXP, DEGREES $ sX5 ale ~ 5 . 0 l@ ea

RNC~LE OF G I D ~ S L I P . DEGREF~

Figuxt 4-6 EEfeck o f Cavard Skrake ZU, Ca~~EPgursr- t i a n 4Q1F-2 With Single VerktcaL Ta.i1 LEF q 2 S Q , bS O,EO Q (a) F a r ~ g - a n d Maroenb?, X$ 6 l e S O s S B 2 S 0 0 eQ.0 0,eO OFF - ~ f - lssoss7es a o el.) o , s o z i ~

Figure 4 - 6 ' (b) Force and Moments, a - 2 1 '

-S eP

RNGLE OOF SIDSSLIP . " D E G R E ~

( c ) Farce and Moments, a 24O ' Figure 4-7 Effect of Canard Strake Z l A , Configuration 401F-5, LEF = 25*., M = 0.80 (a) Force and Moments, a = 1 5 ' 1 8 3 2 V S 0 2 S 0 8 2 0 . 0 0.88 OFF -5 20

RNGLE BOF SIDESLIP ,"DEGREE!?S

Figure 4-7 (b) Force and Moments, a = 2 0 ' - 57 0 ( c ) Force and Moments, a = 2%' Figure 4-7 I -15 - I e -5 1s ' z0

RNGLE BOF S I D E S L I P . "DEGREES

Effect of Forward Vertical T a i l Move- Figure 4 - 8 ment w i t h Canard Strake Z l A , . Configura- tion 401F-5, M = 1.20

Force .--. --. and Moments . -. - . a : .. - 1 0 '

(a)

Figure 4-8 (b) Force and Moments a - 1 5 '

. . 1 1 . + . [ . . . . ,a,, . ,-..pnl.. .. , .. ..t ..pi.. ..+. ..i.. +.*

1 S ::kf{;;<;$];iy& ..+.fa -1.. t,.(-,.,j.. ::i::;;i:/;!;l;,; . . - , . . . 1 , , , , . ,.,.i..~ ; ,4:,i,$];ri ,.,. !..,.,+ ,.,., :;,~,, . ..

' ' I .

-- .-

.l.i.;..i.. .++.I.+!.: 3.3.. ..!.. .+.i..~.~ ..!.I..?. ).. .+l..i ;.

SYH TEST RUN LEF TEF HT RLPHR HlCH CDNF I G ~t:~~:5[;~rli;l-;, :;; iy\:,14,1, ; ; ; , ; .r #.l.. +y.+.!up .r9.1'.q,. ..t..],,l + j.1. . I r , :

+ 1832 5,s 0 0 2e.s 0 . Be " TRFT

1932 589 10 0 8 ~ e . 4 0.88 VTFWD I -15 -18 -5 0 5 18 15 20 ANGLE OF SIDESLIP, DEGREES Figure 4-9 Effect of Forward V e r t i c a l Tat1 Move- ment w i t h Canard StrakeZlA, Configura-

t i o n 401F-5, LEF = lo0, M = 0.80

(a) Force and Moments, . .- a = 20° -

(b) Force and Ehemts, a 2s0 Figure 4 - 9 I -15 -10 - 5 I@ 15 20

ANGLE BOF SIDSESLIP, DEGREES

Figure 4-10 Effect of Forward Vertical Tail liovement with Canard Sgrake Z l A , Configuration 401F-5, LEF = 25 , M = 0.80 (a) Force and 1-foments, a = 2 0 ' Figure 4-10 (b) Force and Moments, a = 2 5 O 57 7 Etfect o f Canard strake 22, Conf igura- Figure 4-11 tisn 401F-2 w i t h T w i n Vertical T a i l s .

& l S S O E 6 O 0 0 l S r B 8.80 OFF .-fB- 1930 72 0 0 0 I 5 , Y 0 . 8 0 218 0 0 0 16.0 .-& 189053 B . 8 0 ES Figure 4-12 Effect of Canard Strakes Z 1 B and Configuration 401F-4, M = 0.80 (a) Force and Moments, a = 16O TEST RUN LEF TEF HT ALPHA NRCH CONFIG 193027 0 8 0 19.3 0.90 OFF

Figure 4b12 (b) Force . ... and . Ploments ,, a - 1 9 '

- i S -10 -S '

R N G L E POF S I D S E S L I P , 'ODEORE&

Figure 4-12 (c) Force and ~ o m e n t s , - 25°

Figure 4 - 1 3 Effect of Canard Strake 23, Configura- tion 401F-4, M = 0.90 --8- 183020 0 8 0 11.0 1.20 OFF I.+- la38 78 o 8 e 10.8 1.20 zie l-m. 1930 48 O ' 0 9 6 . 8 1.28 29 I

-15 -10 - 5

RNGLE BOF S I D ~ S L I P , ' ~ E G R E ~ S S

Figure 4-14 Effect of Canard Strakes Z1B and 23, Configuration 4QJ.F-4, M = 1.20 ,

(a) Force and Moments, a - 11°

Figure 4-14 (b) Force an,d Moments, a - 150

Figure 4-15 Comparison of Canard Strakes ( Z l A , ZlB, Z3), Configuration 401F-5, M = 1.20

(a) Force and Moments, a = lo0

Q I

-15 - 10 -5 0 5 1 B 1 S 20

R N G L E O F S I D E S L I P , DEGREES

Figure 4-15 ( b ) Force and Moments, - lSO

t - z UQ r e oar' x ,

-1s - 1 a -s PNFLE $F SIOSESLIP , l a c ~ ~ ~ ~ ~ ~ 15 eo

Figure 4-16 Comparison of Canard Strakes ( z ~ A , ZlB, 23), Configuration 401F-5, M = 0.80 (a) Force and Moments, = 150 'igure 4-16 (b) Force and Moments, a 20° I -15 -18 -6 28

RNGLE 5~ s I &SL I P . *'DEGRE&

Figure 4-16 (c) Force and Moments, a = 2S0 -15 -18 -5 5 20 RNGLE ?IF S I D E S L I P , ' $ E G R E ~ % E f f e c t of Forebody - Strake Blinding ( Z 4 ) , Figure 4-17 Configuration 401F-5, M = 0.80 (a) Force and Moments, a = 20° .....

SYM TEST RUN LEF TEF HT QLPHR tlRCH CONFIG 0 10 0 0 26.2 0 . 8 0 OFF 1932 457 10 0 0 21.1 6.80 E4 0 0 2 0 . 1 0 . 8 0 ~ ~ 1 1 9 3 2 6 0 8 1 8 Figure 4-17 (b) Increments, a = 20' Figure 4-17 (c) Force and Moments, ff 25* *. % : % x A . - " - 2 , r a L 4 m -.%* RLPHR nncl-I CONFIG 25.2 0.80 OFF -15 -10 -5 8 5 10 15 RNGLE OF S I D E S L I P , DEGREES

Figure 4-17 ( d ) Increments, a - 2 5 O

Effect of Forebody Strakes 24 and Z 5 , Figure 4-18

Conffguration 401F-5, M - 1.20

(a) Force and Moments, a = 100

- .. -

m e * 1 9 3 2 4 0 5 0 0 0 10.2 1 . E C QFF 1032 Y 7 3 0 i3 0 9 . 6 1.20 3: 1 9 3 2 4 7 9 0 0 0 8 . 1 l . Z Q Z S

-1s - 1 0 - s 5 I 0 15 2e

RNGLE $F SIDESLIP. DEGREES

Figure 4-18 (b) Increments, a - lo0

Figure 4-18 ( c ) Force and Moments, a ! l S O

- 15 -10 -5 RNGLE BOF S I D E S L I P , 5 10 DEGREI%

Figure 4-18 ( d ) Increments, = lSO (I) X l a I Figure 4-19 Effect of Fosebodg Strakes 24 and 25,

Configuration 401F-5, EEF - l o 0 , M = 0.80

(a) - Force and Moments, - 15O

*** BRSELINE RUN -15 -10 - 5 5 10 15 20 RNOLE ?IF SIDESLIP. DEGREES Figure 4-19 (b) Increments, a = IS0 -8- 1932 430 10 0 8 20.2 8 . 8 0 OFF

-*- 1932 457 18 0 8 21.1 8 . 8 0 Z4

--Bs 1932 r(53 18 0 43 21.3 0 . 8 0 25 t-a Z?

us x Z I

-15 -10 - 5 5 20

R N O L E ?IF SIDESLIP. ' ~ E G R E & Figure 4-19 (c) Force and Moments, a = 20° Figure 4-19

(d) Increments, a - 20°

SYH TEST RUN LEF TEF HT I832 431 10 8 0 --e- 1932 458 I0 0 0 25.1 0.80 EU *-m. 1932 455 10 0 0 25.6 6.86 E5 Figure 4-19 (e) Force and Moments, a 2 5 6 .. --- --

( f ) increments, ti - 25*

Figure 4-19 Figure 4-20 Effect of Forebody Strake 2 4 , Configura- U F a 15O, M = 0.80 tion 40l.F-5, (a) Force and Moments, - a = 20° - -. -.- ------.-. -----.-. -.- - ......-.,,-.--.-. .

'(b7- Force and-']Eliieenk-2 ,' a = 250

$j..'gure 4-20 -! li -LO -5 1 Ci BQ

RNOLE OOF ~ I D ~ E S L I P , DEGUE&

.$ure 4-21 Effect: of Fox~body Stmke 2 4 an Vertical Taf 1 EEEectiwenass , Canf i g u r a t i o n 4 0 1 ~ - 5 , E 0.80

(a) a . a Force *ye .- -IW_IW_-.w and M o m e n t s a O Q 8 m

-r* m

- I O S E 585 2s s e eo,z o,aa npec,v18

BRSELINE RUN v . 1 5 -5 Fa

RNGLE ?IF $1 D ~ S L I B , " D E G R E ~

Figure 4-21 (b) Strake-sEf ~ncrements , a 20°

BRSELINE R U N - 5 20

R N G L E BOF S I D S E S L I P , ' ' ~ E G R E &

Figure 4-21

(6) Strake-on Increments, a - 200

. .- ". --- . . - .. - " - -. *--"- . -,--*- .

S L ?

we' r E * -15 -I@ -S EO

RNGLE OOF S I D S E S L I P , "DECIRE&

Figure 4-21

(d) Force and Moments, a - 250

1932 536 25 0 0 29 . Y 0 . 5 0 OFFLVT ==r BRSELINE R U N Figure 4-21

(e) Strake-off . - ...--. . Increments, a * 250

**a 1932SB225 B 4 2 5 . 9 0 , 8 o 2V 1832 504 25 0 0 21.9 0 . 8 0 ZYLVT *** BRSELINE R U N

- ANGLE 5 BOF SIDESLIP. "DEGR€& 20

Figure 4-21 ( f ) strake-on' Iacrements, a = 2 5 0

-1s - 10 - 5 20

ANGLE ?IF S I D S E S L I P , '$EGRE&

Figure 4-22 Effect oQ Forebody Strake 25, Confiwra-

- . . t i o n 40kS-4, M - 0.80

(a) Forca urd Moments, a - = 16O ----.As-

i

-15 - 10 -5 RNGLE BOF S I D S E S L I P , ' B D E G R E & 20

- -.-- -- -.-- .

Figure 4-22' (b) ~ i t c e and Nomnts, a - 200

. .

. . . . . . . . . . . . . .

. . .

... . . .i..L.iQt.. ..++.L.J.. ..L++.. ...... A.i.'.. .i.<..i..i. .......... ..l..i..{..i. .,j.i,.+.i. < a .,LILli.. . a .Li.l.. ..iL.l..,.l ..L.;.~i..s.. ..r,i... .A .i... :.pi. L..i..

...... . * . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . " .-.. .. ..---. 1.. ..: .,.;. 4.. ..;.i.i..j.. ..l""pj.. .f..I..1.1. . i . ; ..-. i . . . . , . . . . 9 . ..'.i. I.. ..i:..i..!.. . . . . . . ; . . i s . .. .(. ............. .+.;.!.:!:, "i.....1.;..: ..! ...... - , .;.:. J . :..; f . ~..i.+.;;.~.~..~,+.. . . . . . . . ..r...v-.. ..i.i.~-l..f.~,7"I..P.:sj.~u~"/.. .!..i..:::q :!::I::i:!:. :.i:;:::::. . .

..,.,.7",.., . . . . . .... " . 7 . . 1 w ..r,T,,l",.... .,,-.... . . .,. ,Ti..;, . : . d . . i . . i . .

- SYM TEST RUN LEF TEF HT RLPHA RRCH CONFIG m * . 133027 0 e e 19.3 0 . 8 0 OFF ..i"&+.+.. ..&.<.;..j., ..;.+.~..i..t.(.&.,.i..~&+..iiift ..-.-?.. . .. ,-*.yT"..'fl ,"," '^ . , . , ' 1 " .'"..,..,.

19386R 0 8 B 20.6 0 . 8 0 L5 ) z ] ; i - i + j ; : . , , : rd;;:::: , . . ! ::irft:/;:jk2;::[:if:::/::1 . , , ! . . r , ! . : .

BRSEI-INE RUN I

-1s -10 -5 1 e 1s 20

RNGLE BOF S I D ~ S L I P , DEGREES

Figure 4-22 (c) Increments, a = 200 -------------.. ... ............ - -- Figure 4-22 Force and '~om<-Gts, a = 250 .** 1 9 3 0 2 0 e 0 0 Eu.6 0 . 6 0 1930 69 0 0 8 26.1 Q.CQ *-• BRSELIkE RUN Figure 4-22

(el Increments, a - 250

- .,,.,-.. -. --- ,*...-. -.- -.

OflIGIlV'AL PAGE IS OF POOR QUAT,J?Y I -15 -lB -5 20 ~ ? N G ~ & - ~ F S I ~ - S ~ = I - P - ~ ~ $ E ~ R E ~ S ~ i ~ u r e " * - 4 - 2 3 ~ f i e c t a f Forebody Strake 2 5 , ~ b r i f i ~ v r a - tion401F-4, M - 1 . 2 0 - (a) Force' and Moments, a = 110 n U - j : a s p ' I- 1 9 3 0 2 0 8 0 0 11.0 1.20 OFF is3e6ri e B 8 1 1 . 0 1.20 25 .*a BASELINE RUN Figure ,. _ _ . I . _ _ _ 4-23 ._.- (b) Increments a. = 110 -. .,-I. -- --- - Oltlbli\rAL YAtili: lb OF POOR QUALITY . -.--------- .?. .--------- - -

( c ) Force and Moments, a - 150

~cgure 4 - 2 3 1930 65 0 0 0 1 5 . 1 1.28 Z5 em* BASELINE RUN

Figure 4 - 2 3 ( d ) Increments, a - lSO

. . * . - - .. - -.- - . .

O K N ; , ~ A I ~ IJAGB fS OF POOR QUfiIW - 9 5 -10 - 5

RNGLE $F S I D ~ S L - I ~ ' ,-%€GREG

Effect of Delta Planform Forebody Strakes ~ i ~ u r e 4-24 (Z7-Z10), Configuration 785, LEF = 0, M = 0.50 (a) Force and Moments, a ! l4* Wrn. 1 7 3 0 1 3 8 8 8 0 15.Y 0.88 DFF I -1s -10 -5 20

RNGLE BOF S I D ~ S L I P , "DEGREIS

F i a r e -. . .-. 44-24 -..-- ( b ) -, -- Increments, K = 140

- - --.

!931 2 0 0 0 0 0 20.9 0.88 OFF --&, 1931 172 0 0 0 19.3 0.80 ZT I

-15 -10 - 5 2%

RNGLE OF SIDESLIP, %EGRE&

----"..".% .- -

~ i . ~ u r e 4-24' ' ( c ) ~ o r c i i and Moments, - 200

Figure .- 4-24 fd). Increments, a = 20°

-.---- *.-- . - . . . . - . -

1730 18 B 8 B 25.7 8 . 1 8 OFF .-El-. ie31 1 7 ~ e 0 o 24.3 0.88 27 -1s -18 -5 28

RNGLE BOF SIDESLIP , '@DEGRE&

.- -" -. - ----- ( e ) ~ o r c e and Moments, a! = 24O i?igu~e 4-24 " "'.'. ....', A. .+.. .'.r.;..:. .* ..i. ~ . ; t ....r.;.l.. .:,r.l.;..!.. :;

:.$:;A;:: $2 1 . :i$ +;:i:;/:: ::T

' ' .

,.\.3...;.ia. ..i,.I,?.i.. ..i..i .-.. i.. ..+A.,i,,~.. .,J,i,J..i.. .ill ,. *.i, . J . . ..kt. .jl.b,/.il ..)..z..;.4.. ..i.i..w.. ..],.+.l..p. .t.i..i,.i.. ..l.i..J. I , .d.., I . .-. /.*j,.- .,,. -++. . . - , A : : , , w ~ ~ . y .i.;.+.i.. .,+.+..,+ . ., , .-.. .. . . , , + i . . .....+.+,l., ,. r... ...+. i ,. .;.;,.l+ +.r,,..,., ,-.. . . r ..,...,., '!' !'::-!

.,,.:,i.,,- ..,..!..+..i,. ..+...+. ..;.$.:.. - ; + . ; . , ..l.p,.. ,, ..,. i.:..;..:. .... . , , . , . - 1 ...... ?.. ..,..rp .. ,'.. 1 :. ~ , ~ ; . ; ] . . i q , i . ] . ; r - 7 . . ,,...... ..,.. ,..:.+. -,.: ,.... !.. ..i-+.j.,- .k.i.i(,. .ipii+~.i~ ..i..ryp..:6 .,..,..,.. ,- . . + , g . , l . ... !,.; ,+ vl,.;.J..:.. . ! !..;.-. ... ,b~,; ,..,.: ,. . : ..... .!.. ,, ..

. , ? ? I ! 7 i ! ! i t ! . , . , . . . . . . . . .

SYR E S T ftUN LEF TEF HT mJ=wA tlncn C O N F I G 1931 161)O 0 0 21.7 0 . C 0 O F F 1931 1 7 1 ) @ 0 2 4 . 3 0 . 0 0 ~7 1931 181 0 0 0 1 9 . 1 6.80 ZB S I D E FORCE YRW I N G MOMENT ' = I ROLLING MOMENT' p. -9.19 . -9.85 B.88 -9.le -8.85 8.89 8 . 8 5 8 . 6 -0.W -e.28 O.Q8 0 . 2 8 -6 m- PP Nth w u t h ~ & I ' D f Z ' 4 N O ' O 0 l-'*;r Y O 0 - 0 . " m u mom m c3 = t o m

6.3 P Z

a c w l a fD 8 +',r =t I &I:+' m h) 0 .

I - ' * m g N rr 0 ti

t rn

SYW TEST RUN LEF TEF HT ALPHA MRCH CONFIG 1931 1 6 6 0 0 0 11.5 1 . 2 0 27

-15 -10 - 5 B 6 10 1 S 20

RNGLE O F SIDESLIP, DEGREES Figure -. 4 -. - 2 5 -

(b) - . ..-- Increment$ .--+.--- u.,-~--Lz.*

Figure 4 - 2 5 ( c ) Force and Moments, a 17O

- 15 -10 -5 8 5 I 0 15 28

FJNGt-E OF S IDES1 iP , DEGREES (d . - ) ---- Increments,.- ---. . (y:-.l7*,.

Figure . - -..- 4-25 .- --

+ 173068 5 8 0 20.6 8.80 OFF

- - ~ t 1931 204 s e 0 19.2 0.80 z7 ~-EE)..

1931 299 s e e 18.7 0.80 zle Figure 4-26 . f 2QC (b) Force . --- .,. and -- Moments,. .

ORIGINAL PAGE 1S OF POOR QUALJ'IT ( c ) Increments, a ~ ' 2 0 ~ Figure 4-26

Figure 4 - 2 6 ( d ) Force and Moments, a - 240

TEST RUN LEF TEF HT ALPHR NRCH CDNFIG 1831 2 8 5 5 0 8 2 4 . 1 0 . 8 8 27 1831 210 5 0 8 23.3 8 . 8 0 tl0 Bigure 4-26 ( e ) Increments, = 240 Effect bf Delta Planform Forebody Strakes Figure 4-27 (27, 2101, Configuration 785, IXF - 100, M = 0.80 (a) Force and Moments, a = 140

-, --- -- + - - - - - . - - . a .- -----,,--a -*-. .,-

147 10 0 8 15.5 0.32 CFF 216 16 0 0 1 4 . 1 0.20 27 1931 212 10 8 0 13.8 0.EC 210 ID** BASELINE RUN Figure 4-27 (b) Increments, a = 1 4 O S I D E FORCE ROLLING MOMENT. Y R W I N G MOMENT - B a l e -8.B5 8.89 6-85 -0.19 -8.05 8 - 0 0 9-18 -8.68 -B.Y8 -e.28 0 . 0 0 8.28 - I , Figure 4-27 ( d ) Increments, a = 20° F i g u r e 4-24 ( e ) Force and Moments, a = 24O I -15 -10 -5 0 10 1s 2 J

RNGLE OF SIDESLIP. DEGREES

Figure 4-27 (f) Increments, a = 2 4 O -15 - 10 - 5 0 S 18 15 2 0 RNGLE OF SIDESLIP, DEGREES .

Effect of Delta Planform Forebody Strakes Figure 4-28 (27, 210) Configuration 785, LEF = IS0 M = 0.80 (a) Force - and - Moments, a = 1 4 O

-15 -10 - 5 0 5 10 15 E'3

RNGLE OF SIDESLIP, DEGREES Figure 4-28 (b) Increments, = 140

+ 1730q2 15 0 R 2 0 . 0 6 . 8 8 OFF

.-B).-, 1931 221 15 0 0 19.6 B . 8 8 E7

*-= 1931 225 15 0 B 1B,,$ 8 . 8 8 110

C3 2 8 n .

d?

-

Q I -15 -10 - 5 5 1 0 15 R N G L E $F SIDESLIP, DEGREES Figure 4 - 2 8 (c) Force and Moments, a 19O ORIGINAL PAGE IS OF POOR QUALITY

- 15 - I0 - 5 0 5 10 15 -p c I

FINGLE OF SIDESLIP, DEGREES Figure 4 - 2 8 (d) Increments, a = l ! 1 ° B

-1s - 10 - 5 5 10 1s

RNGLE $F SIDESLIP. D E G R E E S Figure 4-28 (e) Force and Moments, a 24O ORIGINAL PAGE LS OF POOR Q U A L W Figure 4-28 ( f ) Increments, = 2 4 O Figure 4-29 Effect of Forebody Strake 27, Configura- tion 786, M = 1.20 Figure 4-30 Effect a E Forebodp Strake 27, Configura- t i o n 786, LEF = 5O, M : = 0.80 (a) Force and kloments, a' = 200 m m r 1738 1 1 4 5 0 6 2 0 . 5 0 . V )

- 2031 251 5 0 (3 20.3 0.;:. 7'

m** BRSELINE R U N I I - ~ 5 -16 -5 0 5 10 15 ; ' 0 RNGLE OF SIDESLIP, DEGREES

Figure 4-3G (b) Increments, a - 20°

Figure 4 -30 (c) Force and Moh~ents, - 2S0

2 5 . 8 C,CC O f l ' 2031 E52 5 25-3 O , i i ? Z f BRSELINE RUN I t

- 15 - 1 0 -5 15 i' U

RNGLE 0 3 ~ S I D S E S L I P , "DEGREES

Figure 4-30 ( d ) Increments, a = 250 I -1s - t Q -5 1 S

RNGLE OOF s 1 U%SL I P , 'QDEGREES

Figure 4-31 Effect of Forebody Stuske 27, Configura- t i o n 756, LEF = 10Q, M = 0.80 (a) Force and hlaments, = 20° ' i . . : : , ; q : : ;,;,: ; ,.;.:.I: ;;;:::,,i.: .: ::.:..; SYH TEST R U N LEF TEF HT R L P ~ Q flr:l' t'' $7 1 t.

1 ('f " ,,,.,, 1 , .is. ..? ,.. ,.*, ,..: .p. i..i,q.,i.

J . , , . . * , + ; .,*< i 8 . p

i 'I:"*.!. ?.ha\.,l'4 ..:.j.l + .-d.usll I . ,!,*ppy t +.

U r w v 1730 129 10 0 0 20,6 0 ?tl 0 1 ' 1 ' . . . . .

.... - . f ' . ,.,. . . ! . , . i...i..,*.+,

Om i

-;.;A!; - ' 2031 2 ~ 4 10 o a 20.3 o..,i: .?-$ , : ; 8 : o : : ' E:;:.::',:. ::.::.:.': s3:;;a*.,'',' i':'! :' , ,

. 1 *.yrp....i.~k.i

, r + .

* m * BRSELINE R U N I

- 1.5 - l a -5 0 S 111 15 i, Q

RNGLE Q F SIDESLJP, DECREES F i g u r e 4-31 (b) Increments, a = 2U0 we: Z Figure 4 - 3 1 ( c ) Force and Elements, a = 250

- \ -

X I \ r st, i ) S I D E FORCE YFIWING MOMEYT ROLLING MOMENT -@.Ye 4 . 2 8 8-86 , - 8 . 1 0 -@.@5 B.00 -8.85 9.8e 0 . 0 5

09 -

C LJl rt ID r\ rt M 0 1 r . m ; - 0 W D w s o 2 q 0 GI 0 4 r t r rn 0 6 0 I D - m o m SYH TEST RUN LEF TEF HT RLPHA HRCH CONFIG m r * 1730 131 1S 6 0 28.7 8.98 OFF 2831 2U7 IS 0 0 ' 20.3 0 . 8 0 27

- BRSELINE RUN I

- 5

RNGLE BOF S I D S E S L T P , l e ~ ~ ~ ~ ~ S

F i g u r e 4 - 3 2 (b) Increments, a = 200

-15 - 1 Q - S 10 15 22

RNGLE $F S ~ D % S L I P , DEGREES F i g u r e 4-32 ( c ) Force and Eiaments, a = U0 nm* 1738 1 3 2 1 5 B 0 25.9 0 . 8 0 OFF

- 2031 261 15 0 8 25.1 0 . 8 0 Z7

war BASELINE R U N Figure 4 - 3 2 (d) Increments, a = 250 I

-15 - I @ - cj 0 S i b RO

RNGLE OF SIDESLIP, D E G R E ~ E f f e c t o f Ogee P l a n f o ~ m Forabody Strakos Figure 4-33 (214, ZlC, ZlS), Configuxntion 401F-5,

bl - 0.80

(a) Force and Moments, a = 20° Figure 4 - 3 3 ( c ) Force and Moments, a = 2S0 SYH TEST RUN LEF TEF tiT RLPHFI t1$1+'11 I : ? : : ; ' \ (7 29.7 i \ ; i 7 Bill lB3; 608 10 td 8 1932 sss tn 13 k ? PY.9 6,:'t' i l t .

- 15 -10 - S

RNGLE BOF SIDSESLIP , "DEGRE&

.sure 4-34 E f f e c t of Forebody Chines (220, 221) and Canard S t r a k e Z l A , Configuration 401F-10A,

LEF = l o 0 , M = 0.80

(a) Farce and Moments, a = 2 0 ° Figure 4 - 3 4 (b) Force and Moments, a = 25O - 15 -10 - 5 20 R N G L E ?IF s I D'ESL IP , " D E G R E ~ Effect of Forebody Chine 220, Configura- F i g u r e 4 - 3 5 t i ~ n 401F-10A, LEF = 250, M = 0.80 (a) Force and Moments, a = 20° SYtl TEST RUN LEF TEF HT RLPHfl HQCH CDNFIG

+ 2131 9S 25 0 0 2 5 . 8 0 . 8 0 OFF

-*- 2131 64 0 0 2+,9 0 . 8 0 220

-15 -10 - 5 1.

. R N G L E OOF S I D S E S L I P , "DEGREES

( b ) Force and Moments, a - 2S0

~ i g u r e 4-35 -15 -10 -5 5 TO RNGLE $F S I D E S C I P , ' ~ E G R E ~ Figure 4-36 Effect of Forebody Strake Shape (224-227), : Configuration 401F-10A, LEF lo0, M 0.80 (a) Force and Moments, a = 20' srn Trsr RUN LEF TEF HT RLPHFI ~ R C H CONFIG m n r 2131 91 10 0 0 18.9 0 . 8 0 OFF J A

gs

I - J

$

-15 - 1 9 - S e 6 1 B 15

R N G L E OF S I D E S L I P , DEGREES Figure 4 - 3 6 (b) Increments, a 20° Y R W I N G MOMENT SIDE FORCE ROLLING MOMENT -0.40 - e . a 8.89 - @ . I @ -0.85 0.80 - e . ~ s a.08 8 - 0 5 P"' ;; m l C 7. -....,. .?--, *. .*.-.: .*., ", i. -. :.....-, ..,.. .--..

. . . . . . . . . . . .

.,.... ' ..,.. . . . . '..'..<. .?..!..,* ? I * l d i..;..:.; . p , . .." *'.!

. . . . . . . . . . . . .

::~~::.;.::::~-;::~.::~~-;~.;:~:~,~.]:~~:::~ - : i . -:.I : :. _ _ _ - , . . . . . ; : : ; : . . - . . . . . . . . . .

. . .

Q ..,. *.,, ., .. i. i.. ;..i.i ..i .... i . .i., . : . ; , . . i. i..: .,..

i ; !..:. ..ii"l.i. .i;..i..: . C . i 6 2 . . ...i.;.L. :..i.:-.

. . . . . . . . . . . . . . . . . . .

. ..i.;.;_:. .L,;..i.i . : . ; . : . : . .-.i.;.z i . ..&A. .-.>.A.

. . . . . . . . . . . . . . . . . . . . . .

n m . . . . . . . . . . . . . . . . . . . . . .

..:--..p,;. - ," ,..*. .7.9.:-- .*-: ..,--- >.*.. ..: ..?.:.-.

. .

. . . . . . . . . . . . . . . .

m- . . . . . . . . . . . . . . . . . . .

. . . . . . . . . . . . . . . . . . . .

.<..5 .,..,. ,*.,..I .,. ..; ..,..,..,. .,..I .I..* , . , . . ( . . I . . ,..'.*. 8..

N a " ' . . . .

. -;-;..>..: .i i..'; .i.. .iz..; .t t .I.:-:. i .i..i.'. .i . ; . i " .

,L,$ j . 5 , .t.<.i,.i, $t-L$, : : : : - : 7 : 7 . .

- - - . - - - - - - ."?-: - . . . . . . . . . . . . . . . .

<-* :-:- .-**. .- - -... .. - .... "-. ^. :....-. ..*^.?--.

. . . . . . . . . . - i : ; . . . . : _ -

-

. . . . . . . . . . . . . . . . . . . .

'..&.'..'. .'.'.....' '.,-:..* :.., +i .;. :-i.5. ..:.i.+.:.

. . . . . . . . . . . . . . .

_z2.:_.ir . . . i ..... i. .i_: :.. L <.i;.. .... L . . . - . 2 . . ..

. . ;:.: : z . . : . : . . , ..... - - . . . . :.. . + < .- . -... .. -.

: . . .

...... ... ........ . . . ! -..., ..-.2.,.* .! : !

. . . . . . . . .

..... ,..ii.i-. i . . . . . _ . . . . i . :_.-.

. .

. . .

. . . : > . : - -. ... ,-,. ........

. . - _ . . . . . - _ _ . ..^ .- . . -. .. ..^. --. -... .. ......

,. .-.* ..: . .

. -.. ... .,, ...,,,., <.',>I < ..,. i-: .,.. ..:..

. . . . . . .

. . c . !'

. .

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

. . . . . . . . . .

.......... + .. -, -. . . . -. . . . . . . . . ; - c 2- - - .- . . . .

. . . .

..... 2 . t ... ;,, .

:.,. -, z ... :.:;.;..-I . .: !? : . : ; . ,;:: ',:: : ? .

. . . 8 . . . , ..,%.( ,>r,+.r7.' ,.I.+, .,, ,*. r.., , . . . . h , . (..

.s,.~:s+:, ...,C.F. . . , . : . : , . . ..... .i. -,;f;.;.. . , . , . 1 . . , , , .*,?' '.I.. ";.'i.l.. . .t.t *.,.' ... 4 . ,,p.

-\,,.:I,:. pyj.: .!..!,.I . . * . .,.;.&t,*,C. , . .

FlLPHf? m c t i C O N F I G 24.9 0 . 8 0 O F F 25.1 6 . 8 0 z2q

2131 160 10 0 0 24.6 0 . 8 0 Z25 I

- 5 0

R N G L E OF SIDSESLIP, 'EEGREFS

( d ) Increments, a = 25" 67 2

' -15 - 18 '-5 E P

R N G F E 5" S I D ~ S L I P , ' ~ E G R E &

Figure 4-37 Effect sf Forebody Strake Shape (E24-Z26), Configurattion 483F-1QA, EI = 0.90

(a) Farce sad EIomet~ts , lc 200

,---, 2131 169 10 0 0 20.3 0.90 226 *r= BASELINE RUN

-16 -10 - A N G L E 5 b~ S~D?SLIP, %EGRE& ae

Figure 4-37 (b) . --- Increments, -. -.- . a = 20° -. -.

-16 - 1 0 -5 15 20

RNGLE ( b ~ s 1 D%SLI P , ' ~ E G R E E S F i g w e 4 - 3 7 ( c ) Force and Moments, ol = 2SQ 67 5 SYM TEST RlJN LEP TEF HT ALFHn MRCH CONFlG a** a s 1 00 i n o o 2v,o u,oe OFF

- la5 1 0 o n cts,o o.sa za11

--- Et91 10s l o @ 0 CS,O Q,gO 2E!i

F i g u r e 4-37 ( d ) Increments, a = 2SQ 67 6 --I&-- 2131 9U 25 0 0 19.9 0 . 8 0 OFF

..*- 2 l S l i l Q 2 S

0 O 20,l 0 . 8 0 224 ,-Eff- 2131 1 5 6 2 5 o 0 19.7 0.8a 22s -1s -10 -5 2P

RNGLE OOF S I D S E S L I P , ' ' D E G R E ~ ? ~

Effect of Forebodp Strake Shape (224-227), Figure 4 - 3 8 Configuration 401F-lOA, LEF 25', M 0.80 (a) Force and Moments, a = -20° Figure 4 -38 (b) Increments, a 20° .- 15 -10 -5 20

ANGLE BOF s I D ~ S L I P , %EGRE&

( c ) Force and Moments, a = 2 5 O Figure 4 - 3 8 67 9 2131 95 25 B B 2 5 . 0 8 . 8 0 OFF 2131 1 1 1 25 0 B 24.4 8 . 8 8 224 2131 157 25 0 0 25.1 0 . 8 6 225 -5 RNGLE Figure 4 - 3 8 ( d ) Increments, 2S0 B Y m g : & LLB Ri Wo, a' W V) a S Q, Q '9 m --+oh 2230 38Y i Q 0 Q 20,2 0.80 229 I - Z UQ ry 0.9 r : zV3 cl?

-I?

I Q 5 9 d Q -15 -10 -S IS 20

RNGLE OOF SID~SLIP, "?EGREES

F i g u r e 4-39 Effect of Forebody Strake Shape (228-231), Con£ i g u r a t i o n 401F-16, LEF = lQO, M = 0.80 (a) Force and Moments, a = 200 * , .

-15 -10 - 5 0 5 10 L?

RNGLE OF S I D E Y L I P . REGRE& Figure 4 - 3 9 ( b ) Force and Moments, U' = 2S0 -IS -10 -S ANGLE ?IF S I I ~ S L I P , '$EGRE&$ F i g u r e 4 - 3 9 (c) Incremancs, a = 250 Effect of Forebody Strake Shape (228-231), Figure 4-40 Configuration 401F-16, LEF = 25O, M * 0.80 (a) Force and Moments, a = 20° -15 -10 -5 20

RNGLE BOF SIDESLIP, 'BDEGREE%

Figstre 4 -40 (b) Increments , a .=. 206

Figure 4-40 ( c ) Force and Moments, a = 2 5 O ORIGmAL PAGE IS Oli' POOR C3TTA1 T"11 Figure 4-40 ( d ) Increments, a = 250 I-rn z g We: z r I -1s -10 -5 29

RNGLE '%F SIDESLIP, 'BDEGREFS

Figure 4-41 Effect of Forebody S z r ~ k e s 229 and 232, Configuration 401F-16, U F = lo0, M = 0.80 (a) Force and Moments, a = 20° -IS -10 - s 20

R N G C E ' h ~ s I D ~ S L I P , '"DEGREG

Figure 4-41 (b) Force and Moments, a - 25O

-15 - 10 - 5 0 5 10 7 0

A N G L E OF S I D E S L I P , DEGRE& Figure 4 - 4 2 Effect of Forebody Strakes 229 and 232,

Configuration 4 0 1 F - 1 6 , L E F = 2 5 O , M - 0.80

(a) Force and Moments, a = 20° ORIGINAL PAGE I S OF' POOR OTJA T,pllJr I

-15 - 1 0 - RNGLE 5 R ~ F s 1 DSESL I P , "DEGRE& i P

Figure 4-42 (b) Force and Moments, a = 25O -15 -10 -5 10 P O

RNGLE BOF S I D S E S L I P . DEGRE&

Effect of Forebody Strakes 231 and 233, Figure 4 - 4 3 Configuration 401F-16, LEF a lo0, M 0.80 (a) Force, and Moments, a = 20° CBJGrnAx; PAGE I$ Pool? o r r n r TTV RLPHA NRCH CONFIG SYtl TEST RUN LEF TEF HT 20.Q 0.60 251 **R 2330511) 10 0 0 20.2 0 . 6 0 Z33 2330 552 10 0 0 '

*** BRSELlNE R U N I

- 5 20 RNGLE $F S I D ~ E S L I P , '@DEGRE& Figure 4 - 4 3 (b) ~ncrements, a 20° CP I -15 -10 -5 0 5 10 15 kNGLE OF SIDESLIP, DEGREES Figure 4-43 (c) Force and Maments, ff = 2S0 t3xtubU\lAl PAGE IS OF POOR QUAT,ITV rr* 2330515 18 B 0 25.8 0.60 231, 2330533 10 0 0 24.9 0.50 233 *** BRSELINE RUN I Figure 4-43 ( d ) Increments, a = 2S0 Effect a f Borcbody Strakes 231 and 233, Figure 4-44 2 S g , M = 0.80 Configuration 401F-16, LEF

(a) Force' and Moments, a - 2Q0

URlGl.NAL PAGE 1s OF PtMR QUALM'Y r e * BRSELlNE RUN I -15 - 1 0 -5 ea

RNGLE OF s 1 D?~SLI P , "DEGRE&

F i g u r e 4-44 (b) Increments, = 200 I -15 -18 - S 5 15 20 R N G L E ?IF S I D E S L I P , 1 9 ~ ~ ~ ~ Figure 4-44 ( c ) Force and Moments, a = 2S0 UICIGINAL PAGE I>

OF PMR o r r n r I*r\

-Is

-5 RNGLE OOF S I D ~ E S L I P , ''DEGRE&

Figure 4-44 (d) Increments, cv = 25O F i g u r e 4-45 Effect of Fsrebody Strake Shape (263-264, 27 0, M = 0.90

YF-16 + 30.5 Stretch, LEF

(a) Force and Moments, a = lo0 OltlGlNAL PAGg !:It OF POOR QUALITY

F i g u r e 4-45 ( b ) Increments, a = lo0

-15 -10 - 5 0 5 18 15 28

RNGLE OF SIDESLIP, DEGREES Figure 4-46 Effect o f Forebody S trake Shape (263-Z66,Z71),

YF-16 + 30.5 Stretch, LEF = 2S0, M = 0.90

(a) Force and Moments, = 2S0 ORIGINAL Y A G I P

P(-J()T? P V i .""'

- 1.5 - 10 -5

RNGLE 0 0 ~ BI~ESLIP, '@DEGRE&

Figure 4-46 ( b ) ' Increments, a = 2S0 I -15 -10 ~5 15 , PO

RNGLE ? I F S I G S L L P , IODEGREES

F i g u r e 4-47 E f f e c t sf Forebody Strake S i z e (272,275, ~ 8 0 1 ,

YF-16 + 30.5 Stretch, U P = Qo, Pi 0.90

(a) Force and Moments, a = 10" .....

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Figure 4-47 (b) Increments, a = lo0 SYH TEST RUN LEF TEF HT ALPHA MACH CONFIG 3630 1 3 5 2 5 O 0 26.8 Q,9Q 272

@ *- 3630 137 2s 0 Q 2 5 . 5 6.9\? 275

' I

1 3 6 9 0 2 5 7 2 5 0 0 2 B . P ( 1 . 9 0 L B D I -15 - 1 0 -5 2 U

RNGLE OOF s I DSESL I P , 'ODEGREPS

E f f e c t of Forebody Stralce Size (272,275,280), F i g u r e 4-48

YF-16 + 30.5 Stretch, LEF = 25O, M = 0.90

(a) Force and blon~ents, 25O *** BRSELINE RUN -,.I art n . ?

C f ' t - e l

: ?

- 15 -10 -S 0 5 f 0 i? 0-

RNGLE OF S I D E S L ~ P , O E O R E ~ Figure 4-48 (b) Increments, = 2 5 O -15 - l e Figure 4-49 Effect of Nose Strakes 2 7 3 and 274, YF-1G 30.5 Stretch, LEF = 0, M = 0.90 _ 2 MOMENT Y R W I N G MOMENT SIDE FORCE w R O L L I N G MOMENT -@.I@ -8.85 8.80 -@.I@ -8.85 8.80 - 8 . ~ 0 -e.2e e.ee -0.85 8.88 8.85 I r: 2 E: 2

I

Figure 4-51 Effect of Canard Strakes Z 1 D and 281, Y F - 1 6 +

30.5 Sbretch, LEF = 0, M = 0.99 ' -I P . ROLLING MOMENT Y R W I N G MOMENT SIDE FORCE -8.85 6.80 6.m 0.10 - -0.69 -8.~0 -e.20 8.00 e.2e 2 , -0-18 -8.05 9 . 0 8 -8. 18 SYfl TEST RUN LEF TEF HT

-15 - i 0 -5 5 18 20

R N G L E CF SIDESLIP. D E G R E ~

Figure 4-53 Effect of Nose Strake 2100. Fo16, If = 0.90 (a) Force and lloments, a ! = 20 BRIGNAL PAGE I S OF I3OOR OrT T T m ~ i g u r e 4 - 5 3 (b) Force and b m e n t s , a = 25* Reference conditions : 27.87 m2(300 ft2) Figure 4-54 Effect of Nose Strake 2124, F-16, M = 1.20 . .

(a) Force and Moments, a - 20°

ORIGINAL PAGE OF POOR QUALI'

- 15 - 10 - 5 0 5 10 20

RNGLE OF S I D E S L I P , DEGREE

Figure 4-54 (b) Force and Moments, a 2 5 O -15 -16 - 5 0 5 10 15 2 0 RNGLE OF SlDESLIP, DEGREES F i g u r e 4-54 (c) Force and Moments, a = 30° 1 1 V 0 1 1 3 0 0 8 10.8 2.638 OFF 0 1140 223 0 8 8 10.0 2 . 0 0 Zl2* Figure 4 - 5 5 (b) Fsrce and Moments., lo0 Figure 4 - 5 5 (c) Force and. +merits, a = 17O Figure 4-56 E f f e c t of Nose Strake 2128, F-16, M 1.20 (a) Force and.Moments, a = 20° ('R1GrnA-L PAGE IS dli' QIIAI,T77.

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F i g u r e 4 - 5 6 (b) Force and kioriients, a = 300 7 2 1