Numerical prediction of transonic viscous separated flow past an airfoil

Abstract

A method for the numerical treatment of transonic viscous flows past an airfoil has been developed allowing for calculation of both attached flows and flows with large separation regions including shock-induced separation. The method accounts for the entropy correction and the presence of vorticity behind the shock. The method is based on a zonal approach. The computation of the separated-flow regimes is provided by a quasi-simultaneous method of viscous—inviscid interaction. A computer code, called “VISTRAN,” is developed on the basis of this method and extensive comparisons of computed results with experimental data are made.