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MINISTRY OF AVlATlON AERONAUTICAL R
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-2- CONTENTS Int~~duction . . . . .
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General Surves and Conclusions -4-
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-6- and values of M6 < 1) and shock
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-a- have been ~0nce171ed with the f
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- to - APPENDICES Detailed Reviews
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- 12 - where W is the weight of the
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- 14 - In practice, equation (2.1)
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- 16 - nsteady Newtonian theory is
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- 18 - Then the transformed velocit
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- 20 - of a disturbance is of order
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- 22 - u cot cl ucota = . . . (2.35
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- 24 - minimum are that its variati
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- 26 - This simple form of the meth
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t - 28 - and r “” + u’ i + (1
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- 30 - The cut-of-phase component o
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- 32 - indication of their reliabil
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-34- between theory and. experiment
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- 36 - will no longer apply and a s
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- 38 - where m is vehicle mass; p i
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- I+0 - vehicle. (The difference be
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-4z- where C . is the rate of chang
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-44- is to reduce further the range
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46 - APPENDIX IV Review of Flutter
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where z.2 = ll& *.. (4.1) . . . (4.
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- 50 - The thcorctlcal deduction th
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- 52- frequcnoy. Theoretical calcul
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-%- wiierc h and au are the flutter
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- 56 - mean incidence case; but, fo
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- 58 - pressure both for divergence
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- 60 - .h = -. q/MA-1 w3 12(1-l?) E
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a a, A b c cD CL %l %I c% C Q% C mq
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AP 9 P r 'b F a B % R % Be Rex s 9
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Y Y yi 6 F A K - 66 - instantaneous
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Dcfmitions of derivatives "B L, = -
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No. Author(s) 12 Ashley, Holt and Z
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&. Author(sl 36 Moore, F. K. 37 Oli
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- 74 - No. Author(s) Title, etc. 52
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No 65 66 67 68 69 70 . 71 72 73 Aut
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FIG. I (a) Slender wing/body combin
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h ft x From Ref.5 and calculation b
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FIGS.5-7 FIG 5 Axis system for thin
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%‘8 Ro (-X/R; e- -0 \t I FIG. 9 R
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-0.02 0 ’ 0.02 cP 0.04 0.06 O-08
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O- I- 2 - 3 - 4 - ,5- / , / / / /
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FIG. 15 (a) I
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CP (C) of5 = o rrom Flg.ZJof R 19.9
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O-/ 0.12 . 0 OS08 1. CP 0.04 0 -0.0
- Page 99 and 100: O-16 CP o-12 From Ref.29 ;c) M = 6.
- Page 101 and 102: Inviscid theory - - - - Theory with
- Page 103 and 104: I ‘6 2 FIG. I 9 From Fig.3.8 of R
- Page 105 and 106: 1.2 O-8 0.4 0 -0 *4 -0.8 -1.2 0.8 A
- Page 107 and 108: 0.4 0 From Fig. 3.26 of Ref. 26 FIG
- Page 109 and 110: I.0 / / / / ,: kMM; k&I M; A 2-o 0
- Page 111 and 112: k M Mq I.4 O-8 0.6 0.4 0*2 0 -0.2 F
- Page 113 and 114: From Ref. 38 -0.16 (a) Details of m
- Page 115 and 116: IO'4- 5 x 101J- IO' J- 5 x10; 2- 2-
- Page 117 and 118: kit From Fig. 2 of Ref. 48 FIG. 31
- Page 119 and 120: . 2.4 2.0 l-6 K crit l-2 0.0 0.4 0
- Page 121 and 122: M 4 3 2 (,t”, 10-4) Tern OF I Fro
- Page 123 and 124: From Fig.8 of Ref. 56 FIG. 36 50 10
- Page 125 and 126: “f,o 5 I From Ref. 56 I I 0 IO FI
- Page 127 and 128: From Fig.2 in Ref. 57 FIG. 39 ----L
- Page 129 and 130: From Ref 57 0.7 6 0 - - - - - 3% --
- Page 131 and 132: From Ref. 57 o-7. 0.61 0 - - - - 3%
- Page 133 and 134: 6 I i 1 nbol 6 = From Ref.61--/ Tip
- Page 135 and 136: . b 0 oao b FIG .44 c) 0 N 0 N . 0
- Page 137 and 138: FIG. 46 From Fig. 5.1 of Ref. 26 0
- Page 139 and 140: From Ref. 57 n.Al I 0.5 FIG. 48 I I
- Page 141 and 142: From Ref. 57 14 IZ- FIG.50 c - 3% t
- Page 143 and 144: (“f Iaxp w Ah (“f )axp (“f )t
- Page 145 and 146: I From Ref. 65 Modes as in FIG.53 P
- Page 147 and 148: q 5 0 7 6 5 4 From Fink 73 nf Rrf~
- Page 149: 2.1 2 -0 Data taken from Ref. 63 o-
- Page 153 and 154: I From Ref.71 FIG. 62 0 5 IO M 15 2
- Page 155 and 156: 0.00 o-00 FIG. 64 FImm -... Fio~ =
- Page 157 and 158: A.R.C. C.P. No.901 Harch. 1%5 Wood,
- Page 160: 0 Crown copyright 1966 Prmted and p