The influence of viscosity to the parameters of supersonic flow over the wing section

The algorithm for numerical simulation of laminar flows over complex shaped bodies is presented. Block structured grids are used. The time-stepping procedure is used to find steady-state solution of the full Navier-Stokes equations. To achieve higher accuracy of Godunov scheme the piecewise linear distributions of flow variables for the inviscid terms are used, the central differences for approximation of viscous terms are used. The numerical results for the supersonic flow over the wing section under several angles of incidence values is presented. The influence of viscosity value for these results is shown.