Influence of flow conditions over the forebody of a hypersonic air inlet on the flow of air in a boundary-layer bleed channel

In the present paper, we report on the results of a study that was performed as part of the program for developing a method for calculating the flow and the mass-flow-rate coefficient in narrow cylindrical bleed channels under conditions of impingement of a thick boundary layer. For setting the boundary conditions at the inlet boundary of the computational domain, we used the pressure and temperature profiles obtained at the outlet boundary of the simulation domain for the flow around the forebody of a hypersonic air inlet. Numerical modeling of the 3D flow around that forebody was carried out in the range of Mach numbers from 3 to 6 at an angle of attack of 6°. The distributions of static pressure calculated along the symmetry plane and in the transverse direction were compared with experimental data. A satisfactory agreement between the calculated and experimental data is shown. The simulation of the flow was carried out within the framework of the Reynolds-averaged stationary Navier-Stokes equations using the k - ω SST model of turbulence. The obtained distributions of flow parameters and flow streamlines have allowed us to perform an analysis of specific features of the flow structure on the forebody of the model air inlet and in a boundary-layer bleed channel. The calculations showed that, in the examined range of Mach numbers, a sonic flow in boundary-layer bleed channels could be realized to ensure a maximum rate of the mass flow of air through the channels.