Viscous/Inviscid Interaction Procedures for Compressible Aerodynamic Flow Simulations

摘要

Steady transonic flows over a wing ate calculated based on a hierarchical formulation where the potential flows are corrected due to the entropy and vorticity effects of shock waves and/or laminar boundary layers Preliminary results are in agreement with standard Euler and Navier-Stokes calculations. The merits of the present approach are briefly discussed.