Numerical study of the aerodynamic characteristics of a triangular wing at different angles of attack and large Mach numbers

The results of numerical simulation of the external supersonic flow around a triangular wing with a blunted leading edge at Mach numbers 6 and 9, obtained in the framework of a quasi-gas dynamic (QGD) algorithm, are presented. The formulation of the problem at Mach number 9 corresponds to experiments in a wind tunnel. The values of the aerodynamic coefficients obtained at different angles of attack are in good agreement with the experimental data. It is shown that the modeling carried out using more detailed grids is more accurate.