A patched-grid algorithm for the analysis of complex configurations with an implicit, upwind-biased Navier-Stokes solver is presented. Results from both a spatial-flux and a time-flux conservation approach to patching across zonal boundaries are presented. A generalized coordinate transformation with a biquadratic geometric element is used at the zonal interface in order to treat highly stretched viscous grids and arbitrarily shaped zonal boundaries. Applications are made to the F/A-18 forebody-Ieading-edge extension configuration at subsonic, high-alpha conditions. Computed surface flow patterns compare well with ground-based and flight-test results; the large effect of Reynolds number on the forebody flowfield is shown.
Application of a Patched-Grid Algorithm to the F/A-18 Forebody-Leading-Edge Extension Configuration
27th Aerospace Sciences Meeting ; 1989 ; Reno, NV, US
Journal of Aircraft ; 27 , 9
01.09.1990
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Englisch