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5-9 CFD vs. wind tunnel comparison of upper (blue) and lower (red) surface Cp vs. nondimensional chord at 84% span for: Cobalt CFD tip-launcher Grid8 (solid lines), Sellers’ tip AIM-9 wind tunnel model (dashed-dotted lines), and Elbers’ underwing AIM-120 wind tunnel model (open circles). ......................................................................65 5-10 CFD vs. wind tunnel comparison of upper (blue) and lower (red) surface Cp vs. nondimensional chord at 72% span for: Cobalt CFD tip-launcher Grid8 (solid lines), Sellers’ tip AIM-9 wind tunnel model (dashed-dotted lines), and Elbers’ underwing AIM-120 wind tunnel model (open circles). ......................................................................66 5-11 CFD vs. wind tunnel comparison of upper (blue) and lower (red) surface Cp vs. nondimensional chord at 59% span for: Cobalt CFD tip-launcher Grid8 (solid lines), Sellers’ tip AIM-9 wind tunnel model (dashed-dotted lines), and Elbers’ underwing AIM-120 wind tunnel model (open circles). ......................................................................67 5-12 CFD vs. wind tunnel comparison of upper (blue) and lower (red) surface Cp vs. nondimensional chord at 46% span for: Cobalt CFD tip-launcher Grid8 (solid lines), Sellers’ tip AIM-9 wind tunnel model (dashed-dotted lines), and Elbers’ underwing AIM-120 wind tunnel model (open circles). ......................................................................68 5-13 CFD vs. wind tunnel comparison of upper (blue) and lower (red) surface Cp vs. nondimensional chord at 32% span for: Cobalt CFD tip-launcher Grid8 (solid lines), Sellers’ tip AIM-9 wind tunnel model (dashed-dotted lines), and Elbers’ underwing AIM-120 wind tunnel model (open circles). ......................................................................69 6-1 F-16 wing planform with Spanwise (BL) tap locations indicated by green lines. ...........105 6-2 Roll oscillation angle vs. time with numbers 1-9 indicating the instantaneous measurements taken during the oscillatory cycle. ...........................................................105 6-3 DDES of F-16 in sinusoidal rolling motion with instantaneous Mach=1 boundary iso-surface colored by pressure contour for clean-wing Grid0 ........................................106 6-4 DDES of F-16 in sinusoidal rolling motion with instantaneous vorticity magnitude iso-surface colored by pressure contour for clean-wing Grid0 ........................................107 6-5 Instantaneous Cp measurements on F-16 Grid0 clean-wing configurations at 93% span ..................................................................................................................................108 6-6 Instantaneous Cp measurements on F-16 Grid0 clean-wing configurations at 88% span ..................................................................................................................................109 6-7 Lissajous plots of upper surface Cp vs. local displacement during 1Hz roll oscillation for clean-wing Grid0. .......................................................................................................110 6-8 2-D (left column) and 3-D (right column) Lissajous for Grid0 clean-wing 1Hz roll oscillation .........................................................................................................................111 10
6-9 Lissajous plots of upper surface Cp vs. local displacement during 8Hz roll oscillation for clean-wing Grid0. .......................................................................................................112 6-10 2-D (left column) and 3-D (right column) Lissajous for clean-wing Grid0 8Hz roll oscillation .........................................................................................................................113 6-11 Temporal analysis of upper surface Cp for Grid0 8Hz roll oscillation at 93% span vs. 65% chord ........................................................................................................................114 6-12 Temporal analysis of upper surface Cp for Grid0 8Hz roll oscillation at 88% span vs. 69% chord ........................................................................................................................115 6-13 DDES-SARC of F-16 in sinusoidal 8Hz rolling motion with instantaneous Mach=1 boundary iso-surface colored by pressure contour ..........................................................116 6-14 DDES-SARC of F-16 in sinusoidal 8Hz rolling motion with instantaneous vorticity magnitude iso-surface colored by pressure contour.........................................................117 6-15 Instantaneous Cp measurements on F-16 wing at 98% span for 8Hz roll ........................118 6-16 Instantaneous Cp measurements on F-16 wing at 93% span for 8Hz roll ........................119 6-17 Instantaneous Cp measurements on F-16 wing at 88% span for 8Hz roll ........................120 6-18 Lissajous plots of upper surface Cp vs. local displacement during 8Hz roll oscillation for tip-launcher Grid4. .....................................................................................................121 6-19 2-D (left column) and 3-D (right column) Lissajous for Grid4 tip-launcher 8Hz roll oscillation case .................................................................................................................122 6-20 Temporal analysis of upper surface Cp for Grid4 8Hz roll oscillation at 98% span vs. 44% chord. .......................................................................................................................123 6-21 Temporal analysis of upper surface Cp for Grid4 8Hz roll oscillation at 93% span vs. 67% chord. .......................................................................................................................124 6-22 Temporal analysis of upper surface Cp for Grid4 8Hz roll oscillation at 88% span vs. 70% chord. .......................................................................................................................125 6-23 Pitch oscillation angle vs. time with numbers 1-9 indicating the instantaneous measurements taken during the oscillatory cycle. ...........................................................126 6-24 DDES-SARC of F-16 in sinusoidal pitching motion with instantaneous Mach=1 boundary iso-surface colored by pressure for clean-wing cases ......................................127 6-25 DDES-SARC of F-16 in sinusoidal pitching motion with instantaneous vorticity magnitude iso-surface colored by pressure for clean-wing cases ....................................128 6-26 Instantaneous Cp measurements on F-16 wing at 98% span ............................................129 11
Page 1 and 2: TEMPORAL ANALYSIS OF TRANSONIC FLOW
Page 3 and 4: To Dodjie 3
Page 5 and 6: TABLE OF CONTENTS ACKNOWLEDGMENTS .
Page 7 and 8: Summary ...........................
Page 9: LIST OF FIGURES Figure page 2-1 F-1
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
Page 87 and 88:
near 70% chord and the second near
Page 89 and 90:
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
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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
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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 (
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Page 129 and 130:
Page 131 and 132:
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A B D Figure 6-40. DDES of F-16 in
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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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