VISCOUS SUPERSONIC-FLOW COMPUTATIONS OVER A DELTA-RECTANGULAR WING WITH SLANTING SURFACES

A three-dimensional Navier-Stokes code has been applied to calculate flowfields over sharp-edged delta-rectangular wing with slanting surfaces at supersonic conditions. The steady-state solutions were obtained by solving the full compressible Reynolds-averaged Navier-Stokes equations on a three-dimensional multizone grid using the MacCormack finite-volume explicit algorithm and the Baldwin-Lomax turbulence model. The computations were carried out at a fixed freestream Mach number and at various angles of attack. Grid resolution effects were also investigated. The numerical computations were found to agree well with the experimental data.