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This material is declared a w<strong>or</strong>k <strong>of</strong> the U.S. Government and is not subject to copyright protection in the United States. 2
To Dodjie 3
Page 1: TEMPORAL ANALYSIS OF TRANSONIC FLOW
Page 5 and 6: TABLE OF CONTENTS ACKNOWLEDGMENTS .
Page 7 and 8: Summary ...........................
Page 9 and 10: LIST OF FIGURES Figure page 2-1 F-1
Page 11 and 12: 6-9 Lissajous plots of upper surfac
Page 13 and 14: 6-45 2-D (left column) and 3-D (rig
Page 15 and 16: incrementally since this capability
Page 17 and 18: are not sufficient to provide an an
Page 19 and 20: 4. Contribute to the work of others
Page 21 and 22: Classical aircraft flutter is chara
Page 23 and 24: Popular methods for finding the sol
Page 25 and 26: LCO amplitude but not the mechanism
Page 27 and 28: speed for the particular configurat
Page 29 and 30: Denegri 23 explains the flutter fli
Page 31 and 32: Doublet-lattice Denegri 1, 7,12,13
Page 33 and 34: Batina’s work and uses an F-16 ha
Page 35 and 36: As a result of Denegri’s previous
Page 37 and 38: Figure 2-1. F-16 store stations. Fi
Page 39 and 40: Figure 2-5. Flutter flight test bui
Page 41 and 42: Stokes (RANS) equations on hybrid u
Page 43 and 44: CHAPTER 4 ANALYSIS TECHNIQUES Intro
Page 45 and 46: time-localization cannot be determi
Page 47 and 48: A B C D E Figure 4-3. Analysis of s
Page 49 and 50: (CFD) analyses in order to capture
Page 51 and 52: the appropriate time step for the n
Page 53 and 54:
Wing1, is the wing-only (no fuselag
Page 55 and 56:
similar to DES but with modificatio
Page 57 and 58:
Figure 5-1. Time step comparison of
Page 59 and 60:
A B Figure 5-3. Flow results for 8
Page 61 and 62:
A B Figure 5-5. Flow results for 8
Page 63 and 64:
Figure 5-7. Turbulence model compar
Page 65 and 66:
Figure 5-9. CFD vs. wind tunnel com
Page 67 and 68:
Figure 5-11. CFD vs. wind tunnel co
Page 69 and 70:
Figure 5-13. CFD vs. wind tunnel co
Page 71 and 72:
server cluster comprised of 5,120 p
Page 73 and 74:
of oscillation. The 88% span locati
Page 75 and 76:
since it is proportional to lift, a
Page 77 and 78:
of phase. Figure 6-10 B) and D) are
Page 79 and 80:
The instantaneous Cp measurements p
Page 81 and 82:
D Lissajous plots with time being t
Page 83 and 84:
frequency of 8Hz. The wavelet plot
Page 85 and 86:
vortex is observed travelling outbo
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near 70% chord and the second near
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expected from a lift curve slope. A
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shape of this Lissajous is nonlinea
Page 93 and 94:
occurring at harmonics, and assumes
Page 95 and 96:
the same direction of rotation on t
Page 97 and 98:
the roll cycle, and the black arrow
Page 99 and 100:
B) shows the fast Fourier transform
Page 101 and 102:
is that shock separation aft of the
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on the upper surface, a much larger
Page 105 and 106:
Figure 6-1. F-16 wing planform with
Page 107 and 108:
A C B Figure 6-4. DDES of F-16 in s
Page 109 and 110:
Cp (Non-dimensional) Cp (Non-dimens
Page 111 and 112:
-Cp (Non-dimensional) A -Cp (Non-di
Page 113 and 114:
Page 115 and 116:
-Cp (Non-dimensional) A Time (sec)
Page 117 and 118:
A B Figure 6-14. DDES-SARC of F-16
Page 119 and 120:
Page 121 and 122:
Figure 6-18. Lissajous plots of upp
Page 123 and 124:
-Cp (Non-dimensional) Frequency (Hz
Page 125 and 126:
-Cp (Non-dimensional) A Frequency (
Page 127 and 128:
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Page 131 and 132:
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Page 135 and 136:
Page 137 and 138:
Page 139 and 140:
Page 141 and 142:
Page 143 and 144:
A B D Figure 6-40. DDES of F-16 in
Page 145 and 146:
Page 147 and 148:
Page 149 and 150:
Page 151 and 152:
Page 153 and 154:
Page 155 and 156:
Page 157 and 158:
Impact on Future Design of Aircraft
Page 159 and 160:
The size of the Mach=1 iso-surface
Page 161 and 162:
these cases in order to identify th
Page 163 and 164:
15. Dawson, K. S., and Sussinham, J
Page 165 and 166:
41. Thomas, J. P., Dowell, E. H., a
Page 167 and 168:
67. Cunningham, A. M., Jr., and den
Page 169 and 170:
93. Parker, G. H., Maple, R. C., an
Page 171 and 172:
121. Travin, A. K., Shur, M. L., Sp
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