Viscid turbulent flows over the hypersonic inlet at the throttling regimes

The method and applied software, developed for the numerical simulation of viscid turbulent flow over the hypersonic inlet at the throttling regimes, are considered. The method is based on the numerical integration of the full Navier–Stokes system of equations. The method is verified by the means of the comparison of calculated and experimental results (integral features of the inlet and the boundary of the stable flow). The condition of flow stability is formulated to detect the corner point of the throttling dependence in the calculation.