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A B Figure 6-39. DDES of F-16 in 8Hz sinusoidal pitching motion with instantaneous Mach=1 boundary iso-surface colored by pressure for: Grid8 tip-launcher case A) Upper & B) Lower surfaces and Grid9 clean-wing case C) Upper & D) Lower surfaces. 142 C D
A B D Figure 6-40. DDES of F-16 in 8Hz sinusoidal pitching motion with instantaneous vorticity magnitude iso-surface colored by pressure for: Grid8 tip-launcher case A) upper & B) lower surfaces and Grid9 clean-wing case C) upper & D) lower surfaces. 143 C
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TEMPORAL ANALYSIS OF TRANSONIC FLOW
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To Dodjie 3
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TABLE OF CONTENTS ACKNOWLEDGMENTS .
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Summary ...........................
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LIST OF FIGURES Figure page 2-1 F-1
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6-9 Lissajous plots of upper surfac
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6-45 2-D (left column) and 3-D (rig
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incrementally since this capability
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are not sufficient to provide an an
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4. Contribute to the work of others
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Classical aircraft flutter is chara
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Popular methods for finding the sol
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LCO amplitude but not the mechanism
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speed for the particular configurat
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Denegri 23 explains the flutter fli
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Doublet-lattice Denegri 1, 7,12,13
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Batina’s work and uses an F-16 ha
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As a result of Denegri’s previous
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Figure 2-1. F-16 store stations. Fi
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Figure 2-5. Flutter flight test bui
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Stokes (RANS) equations on hybrid u
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CHAPTER 4 ANALYSIS TECHNIQUES Intro
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time-localization cannot be determi
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A B C D E Figure 4-3. Analysis of s
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(CFD) analyses in order to capture
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the appropriate time step for the n
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Wing1, is the wing-only (no fuselag
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similar to DES but with modificatio
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Figure 5-1. Time step comparison of
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A B Figure 5-3. Flow results for 8
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A B Figure 5-5. Flow results for 8
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Figure 5-7. Turbulence model compar
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Figure 5-9. CFD vs. wind tunnel com
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Figure 5-11. CFD vs. wind tunnel co
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Figure 5-13. CFD vs. wind tunnel co
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server cluster comprised of 5,120 p
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of oscillation. The 88% span locati
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since it is proportional to lift, a
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of phase. Figure 6-10 B) and D) are
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The instantaneous Cp measurements p
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D Lissajous plots with time being t
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frequency of 8Hz. The wavelet plot
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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
Page 91 and 92: 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
Page 103 and 104: 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 115 and 116: -Cp (Non-dimensional) A Time (sec)
Page 117 and 118: A B Figure 6-14. DDES-SARC of F-16
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 141: -Cp (Non-dimensional) A Time (sec)
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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