Numerical simulation of viscous supersonic flow over a generic fighter configuration
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Chaussee, D. S.↗
Engineering topics
Wai, J.
Publications and source records attributed to Wai, J..
Numerical simulation of viscous supersonic flow over a generic fighter configuration
A procedure is presented, as well as some results, to calculate the flow over a generic fighter configuration. A parabolized marching Navier-Stokes code is used to obtain the solution over a wing-canopy body. The flow conditions simulate supersonic cruise with a freestream Mach number of 2.169 and angles of attack of 4 and 10 deg. The body surface is considered to be an adiabatic wall and the flow is assumed to be turbulent for the given Reynolds number.
Chaussee, D. S.↗
Higher-Order Panel Method for Aerodynamic Flow Analysis
PANAIR uses high-order panel method to predict inviscid subsonic or supersonic flows about arbitrary configuration. Panel method solves linear partial differential equation numerically by approximating configuration surface with panels on which unknown "singularity strengths" are defined. PANAIR includes advanced software technology as well as advanced aerodynamic technology.
Erickson, L.↗