Calculations for a Generic Fighter at Supersonic High-Lift Conditions,
BOEING MILITARY AIRPLANE CO SEATTLE WA
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The parabolized NavierStokes method was used to calculate the flow over a generic fighter configuration with a canard and underwing nacelles at supersonic high lift conditions. The calculated pressure distributions agreed closely with experiments, but the pitot pressure profile predictions for the boundary layer were less satisfactory largely due to an inadequate mesh in the viscous sublayer.