Thin-layer full Navier-Stokes simulations over a supersonic delta wing
Steady flowfields describing the flow over a 75-deg swept delta wing at M ∞=1.95 and Re=4.48×10 6 were simulated at α=20 and 30 deg using two computer codes. Comparisons were made between calculations using 1) the laminar and turbulent thin-layer Navier-Stokes equations, and 2)laminar thin-layer and Navier-Stokes equations.