The NASA-Ames/Boeing unsteady thin-layer Navier-Stokes code was used to calculate a generic wing/fuselage configuration at a Mach number of 25. Calculations were obtained with perfect gas and with chemical equilibrium air assumption; the surface temperature were prescribed, the results of the two solutions are compared in terms of distribution of pressure, density, temperature, Mach number, ratio of specific heat and heat transfer.
Navier-Stokes simulation of a hypersonic generic wing/fuselage
Allgemeine Navier-Stokes Simulation fuer hypersonisch umstroemte Tragfluegel-Rumpf Verbindungen
AIAA-Papers ; Jun ; 1-12
1987
12 Seiten, 12 Bilder, 6 Quellen
Aufsatz (Konferenz)
Englisch
MACHZAHL , NAVIER-STOKES-GLEICHUNG , TRAGFLUEGEL , FLUGZEUGRUMPF , OBERFLAECHENTEMPERATUR , DRUCKVERTEILUNG , WAERMEUEBERTRAGUNG , REALES GAS , NUMERISCHES VERFAHREN , HYPERSONISCHE STROEMUNG , INSTATIONAERE STROEMUNG , SIMULATIONSPROGRAMM , TRAGFLUEGELUMSTROEMUNG , IDEALES GAS , GASDICHTE , WAERMEKAPAZITAET
Multiblock Navier-Stokes solver for wing/fuselage transport aircraft
Tema Archiv | 2002
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