Direct numerical simulation of supersonic (Mach number is 1.5) viscous heat-conducting gas flow past a body of revolution (standard HB-2 model) at an angle of attack 29° is carried out. The calculation results make it possible to resolve the general structure of shocks around the body and to obtain a good agreement of the stagnation parameters and the aerodynamic coefficients with theoretical and experimental data. The simulation was carried out on the basis of a quasi-gas dynamic (QGD) algorithm, that describes not only stationary and symmetric, but also non-stationary and asymmetric vortex zones that develop in flow. In this case, no additional turbulent viscosity is used in the calculations. It is shown that reducing the artificial dissipation coefficients in the QGD algorithm increases the accuracy of the modeling, bringing the calculated aerodynamic coefficients closer to the experimental data.
Shirokov et al. (Wed,) studied this question.