- 74 - No. Author(s) Title, etc. 52 Nonweiler, T. The control and stability <strong>of</strong> glider aircraft at hypersonic speeds. A.R.C.21 301 7th October, 1959. 53 Peterson, Victor L. Motions <strong>of</strong> a short IO" blunted cone entering a Martian atmosuhere at arbitrarv angles <strong>of</strong> attack and arbitrary pitching rates. NASA TN D-l 3.26. May, 1962. 54 Taylor, Lawrence W. Jr. Flight controllability limits and related human and transfer functions as determined from simulator Day, Richard E. and free flight tests. NASA TN D-746. May, 1961. References (Appendix IVY
&. 55 56 57 58 59 60 61 62 63 64 Author(s) Bisplingh<strong>of</strong>f, R. L. Chawla, Jagannath P. Morgan, Homer G., Runyan, Harry L. and Huckel, Vera Runyan, Harry L. and Morgan, Homer G. Hanson, Perry W. Goete, Robert C. Young, Lou S. Bisplingh<strong>of</strong>f, R. L. and Ashley, Holt Sewall, John L., Hess, Robert W. and Watkins, Charles E. Morgan, Homer G. Huckel, Vera and Runyan, Harry L. - 75 - References (Appendix IV) Title. etc. Some structural and aeroelastic considerations <strong>of</strong> high-speed flight. 19th Wright Brothers Lecture. J.Ae.Sci. Vo1.23, No.4. April, 1956. pp.289-329. Aeroelastio instability at high Maoh number. J.Ae.Sci. Vo1.25, No.4. April, 1958. pp.246-258. Theoretical considerations <strong>of</strong> flutter at high Mach numbers. J.Ae.Sci. Vo1.25, No.6. June, 1958. pp,371-331. Flutter at very high speeds. NASA TN D-942. August, 1961. Aerodynamio effects <strong>of</strong> sane configuration variables on the aeroelastic characteristics <strong>of</strong> lifting surfaces at Mach numbers from 0.7 to 6-86. NASA TN D-984. November, 1961. Effects <strong>of</strong> leading-edge bluntness on flutter characteristics <strong>of</strong> some square-planform doublewedge airfoils at a Mach number <strong>of</strong> 15.4. NASA TN D-1407. October, 1962. Effects <strong>of</strong> angle <strong>of</strong> attack and thickness ratio on flutter <strong>of</strong> a rigid unswept diamond-airfoil section dng at a Mach number <strong>of</strong> IO-O. NASA TN D-1380. August, 1962. Principles <strong>of</strong> aercalasticity. John Wiley & Sons Inc. 1962. Analytical and experimental investigations <strong>of</strong> flutter and divergence <strong>of</strong> spring mounted cone configurations at supersonic speeds. NASA TN D-1021. April, 1962. Procedure for calculating flutter athigh supersonic speeds, including camber deflections, and comparison with experimental results. NACA TN 4335. September, 1958. 65./
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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
- 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 78 and 79: No 65 66 67 68 69 70 . 71 72 73 Aut
- Page 81 and 82: FIG. I (a) Slender wing/body combin
- Page 83 and 84: h ft x From Ref.5 and calculation b
- Page 85 and 86: FIGS.5-7 FIG 5 Axis system for thin
- Page 87 and 88: %‘8 Ro (-X/R; e- -0 \t I FIG. 9 R
- Page 89 and 90: -0.02 0 ’ 0.02 cP 0.04 0.06 O-08
- Page 91 and 92: O- I- 2 - 3 - 4 - ,5- / , / / / /
- Page 93 and 94: FIG. 15 (a) I
- Page 95 and 96: CP (C) of5 = o rrom Flg.ZJof R 19.9
- Page 97 and 98: 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
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From Ref 57 0.7 6 0 - - - - - 3% --
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From Ref. 57 o-7. 0.61 0 - - - - 3%
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6 I i 1 nbol 6 = From Ref.61--/ Tip
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. 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
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From Ref. 57 n.Al I 0.5 FIG. 48 I I
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From Ref. 57 14 IZ- FIG.50 c - 3% t
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(“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~
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2.1 2 -0 Data taken from Ref. 63 o-
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$3 i I a( I.2 (Ib/sq 1 in.) ’ ‘
- Page 153 and 154:
I From Ref.71 FIG. 62 0 5 IO M 15 2
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0.00 o-00 FIG. 64 FImm -... Fio~ =
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A.R.C. C.P. No.901 Harch. 1%5 Wood,
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0 Crown copyright 1966 Prmted and p