Two approaches to calculate turbulent vortical flows over delta wing configurations are illustrated. The first is for a simple delta wing at low speeds using the boundary layer approximation to treat the effects of the secondary separation. The second is for the supersonic case of a generic fighter using the NASA Ames parabolized Navier/Stokes method. Test/theory comparisons are given in both cases.
Viscous vortical flow calculations over delta wings
01.07.1986
Aufsatz (Konferenz)
Keine Angabe
Englisch
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