An aerodynamic prediction technique based on the steady form of the full-potential equation has been applied to a variety of three-dimensional supersonic flow problems exhibiting embedded subsonic regions. A conservative switching scheme is employed to transition from the supersonic relaxation algorithm, and vice versa. Numerical solutions are obtained for a number of complex configurations, including advanced tactical fighter, Langley canard-wing fighter configuration, isolated shuttle orbiter, and mated shuttle orbiter configuration with external tank. The computed results are in good agreement with available experimental data.
Computation of supersonic flows over three-dimensional configurations
Journal of Aircraft ; 22
1985-12-01
Miscellaneous
No indication
English
Computation of three-dimensional turbulent separated flows at supersonic speeds
Tema Archive | 1979
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