Numerical simulation of supersonic flows in the wing wake and its interaction with crossing shock waves

The results of numerical simulation of supersonic flow in the wing wake and its interaction with shock waves investigation are presented. The system of couple counter wedges with a sharp edge has been used for the formation of shock waves of varying intensity. Investigation of regular and Mach interaction of shock waves has been performed. Calculations have been performed on a multiprocessor computer system K-100 in KIAM RAS. Experiments were carried out in a supersonic wind tunnel T–325 (ITAM SB RAS) at the Mach number 3.