A Survey of Unsteady Hypersonic Flow Problems

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FIG. I (a) Slender wing/body combination -3 /-Tz7-\ (9 Caret wing =q ~-3 \ Plane shock <strong>Hypersonic</strong> cruise configurations
Page 1:
MINISTRY OF AVlATlON AERONAUTICAL R
Page 4 and 5:
-2- CONTENTS Int~~duction . . . . .
Page 6 and 7:
General Surves and Conclusions -4-
Page 8 and 9:
-6- and values of M6 < 1) and shock
Page 10 and 11:
-a- have been ~0nce171ed with the f
Page 12 and 13:
- to - APPENDICES Detailed Reviews
Page 14 and 15:
- 12 - where W is the weight of the
Page 16 and 17:
- 14 - In practice, equation (2.1)
Page 18 and 19:
- 16 - nsteady Newtonian theory is
Page 20 and 21:
- 18 - Then the transformed velocit
Page 22 and 23:
- 20 - of a disturbance is of order
Page 24 and 25:
- 22 - u cot cl ucota = . . . (2.35
Page 26 and 27:
- 24 - minimum are that its variati
Page 28 and 29:
- 26 - This simple form of the meth
Page 30 and 31: t - 28 - and r “” + u’ i + (1
Page 32 and 33: - 30 - The cut-of-phase component o
Page 34 and 35: - 32 - indication of their reliabil
Page 36 and 37: -34- between theory and. experiment
Page 38 and 39: - 36 - will no longer apply and a s
Page 40 and 41: - 38 - where m is vehicle mass; p i
Page 42 and 43: - I+0 - vehicle. (The difference be
Page 44 and 45: -4z- where C . is the rate of chang
Page 46 and 47: -44- is to reduce further the range
Page 48 and 49: 46 - APPENDIX IV Review of Flutter
Page 50 and 51: where z.2 = ll& *.. (4.1) . . . (4.
Page 52 and 53: - 50 - The thcorctlcal deduction th
Page 54 and 55: - 52- frequcnoy. Theoretical calcul
Page 56 and 57: -%- wiierc h and au are the flutter
Page 58 and 59: - 56 - mean incidence case; but, fo
Page 60 and 61: - 58 - pressure both for divergence
Page 62 and 63: - 60 - .h = -. q/MA-1 w3 12(1-l?) E
Page 64 and 65: a a, A b c cD CL %l %I c% C Q% C mq
Page 66 and 67: AP 9 P r 'b F a B % R % Be Rex s 9
Page 68 and 69: Y Y yi 6 F A K - 66 - instantaneous
Page 70 and 71: Dcfmitions of derivatives "B L, = -
Page 72 and 73: No. Author(s) 12 Ashley, Holt and Z
Page 74 and 75: &. Author(sl 36 Moore, F. K. 37 Oli
Page 76 and 77: - 74 - No. Author(s) Title, etc. 52
Page 78 and 79: No 65 66 67 68 69 70 . 71 72 73 Aut
Page 82 and 83: (0) Bluff reentry shapes : L/D=l/2
Page 84 and 85: ft x 300 :0-3 200 Lifting exit J I
Page 86 and 87: 0 1 0 FIG. 8 Rtzaroduct?d from Fia
Page 88 and 89: -0.00 0 cP 0.04 O.08 0.12 0.16 .//
Page 90 and 91: -0002 0 0.02 v 1 0 04. // /p r t -
Page 92 and 93: -0.02 0 o-02 CP 0.04 0.06 0.00 0.10
Page 94 and 95: FIG. 15 (b)
Page 96 and 97: 0.4 1.6 0 -I--+ I I ./-’ 4 .- :al
Page 98 and 99: 0.20 From Ref 29 (b) M=5XIS,itd = 3
Page 100 and 101: 0 I From Ref. 29 W as -00, Lid - 3
Page 102 and 103: From Fig. 3.1 of Ref. 26 Top view-
Page 104 and 105: 4-o 3.6 3.2 FIG. 20 From Fig. 3.13
Page 106 and 107: 4-~,From,Fig. 4-4tl----T 0.0 0.4 3
Page 108 and 109: kM L2 From Fig. 3.2 of Ref. I9 5 0.
Page 110 and 111: FIG.26 ‘8 of Ref. 17 Strong shock
Page 112 and 113: From Fig. I2 of Ref. 37 I.2 - - - -
Page 114 and 115: U 30 25 20 I- fl/secXl0 ,-: IS IO 5
Page 116 and 117: Id 5 x Id 50 IO 5 I FIG. 30 (c) Aer
Page 118 and 119: -"0 ai OS6 u 0'4 a 0 aq ii I OT O-8
Page 120 and 121: W/CDS = 3Olb/ft’ O-8. ai = initia
Page 122 and 123: U ( bw, J 12 IC 0 8 t 4 2 From Ref.
Page 124 and 125: 2 4- 2 2i baa I 2. I O- 0; 4 0 6- F
Page 126 and 127: pr 0, L!!k, “f, r From Rof.56 FIG
Page 128 and 129: 8 7 6 2 I (I Froa Ret 57 FIG. 40 .
Page 130 and 131:
From Ref. 57 o-7 0.6 t - - - - - 3
Page 132 and 133:
I I FIG. 41 (dl From Ref. 57 0.7 O-
Page 134 and 135:
From Ref 58 6. 4 b%c 4 a , rrp 2 d=
Page 136 and 137:
“f boa 0 5 4 3 2 I From Ref. 56 D
Page 138 and 139:
From Fig. 5 of Ref.61 FIG. 47 0 2 4
Page 140 and 141:
From Ret. 57 FIG. 49 “!-ryfzy 7 6
Page 142 and 143:
From Refs 59 & 60 I? e II IO L.E.ro
Page 144 and 145:
J!L bw2 From Ref. 65 Mode I: flexur
Page 146 and 147:
From Fig.5 of Ref 58 ) ] Unstable 1
Page 148 and 149:
From Ref .57 FIG .57 0.6) I / . I I
Page 150 and 151:
FIG. 59 Data taken tram Ref. 63 2.8
Page 152 and 153:
,010 From Ref. 70 FIG. 61 0 I 2 3 4
Page 154 and 155:
‘400 1200 800 2aL3 BD 600 t From
Page 156 and 157:
ft . c 0 40016 a FIG.6.5. Fig. 18 f
Page 158:
Ill stnx%ul-e. the report cOI191sts
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A Survey of Unsteady Hypersonic Flow Problems

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