NUMERICAL SIMULATION OF INCOMPRESSIBLE VISCOUS FLOW OVER A DELTA WING AT HIGH ANGLE OF ATTACK

The choice of the pseudo compressiblility parameter β is investigated and a function form of β which accelerates the convergence effectively is presented. The numerical simulation of vortical flow about a 70° delta wing is made by solving the incompressible Navier Stokes equations. The agreement of calculated results with the experimental data is favourable. The physical aspects of vortical flow of the delta wing at high angles of attack are analysed.