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LIST OF FIGURES
Figure page
2-1 F-16 store stations. .............................................................................................................37
2-2 F-16 doublet lattice aerodynamic model ............................................................................37
2-3 F-16 NASTRAN structural model. ....................................................................................38
2-4 Accelerometer locations on F-16 for flight testing. ...........................................................38
2-5 Flutter flight test build-up procedure for altitude vs. Mach vs. calibrated air speed. ........39
4-1 Lissajous phase relationships for various frequency ratios................................................46
4-2 Morlet mother wavelet. ......................................................................................................46
4-3 Analysis of standard 20 Hz sinusoid ..................................................................................47
5-1 Time step comparison of upper surface Cp vs. non-dimensional chord at 88% span
for high sampling rate in red and low sampling rate in blue. ............................................57
5-2 Viscous, unstructured, full-Scale, F-16 surface mesh on left and computational mesh
at 88% span on right. .........................................................................................................58
5-3 Flow results for 8 Hz ± 0.5° pitch oscillations on clean-wing grids: Grid0 on left and
Grid9 on right. ....................................................................................................................59
5-4 Geometric convergence comparison of upper (blue) and lower surface (red) Cp vs.
non-dimensional chord at 93% span for clean-wing grids: coarse Grid0 (dashed
lines) and fine Grid9 (solid lines). .....................................................................................60
5-5 Flow results for 8 Hz ±0.5° pitch oscillations on tip-launcher grids: Grid4 on left and
Grid8 on right. ....................................................................................................................61
5-6 Geometric convergence comparison of upper (blue) and lower surface (red) Cp vs.
non-dimensional chord at 93% span for tip-launcher grids: coarse Grid4 (dashed
lines) and fine Grid8 (solid lines). .....................................................................................62
5-7 Turbulence model comparison of upper (blue) and lower surface (red) Cp vs. nondimensional
chord at 88% span for wing-only Wing1 grid: SARC-DDES (solid
lines), SA-DDES (dotted lines), and SST-DES (dashes lines). .........................................63
5-8 CFD vs. wind tunnel comparison of upper (blue) and lower (red) surface Cp vs. nondimensional
chord at 96% 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). ......................................................................64
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