Flow features in a hypersonic module with a compact cross-section

Abstract

A model of a hypersonic air intake based on the principle of compression along the directions of the captured jet converging in space is studied. Such an air intake allows a high compression ratio and a compact section of the internal channel, which simplifies the heat protection of the air intake and the combustion chamber. Experimental studies were carried out in a pulsed wind tunnel IT-302M for Mach number M = 6 - 8 in the range of angles of attack from 0° to 8°. Numerical simulation has been performed based on solving the full averaged Navier-Stokes equations, supplemented k-w turbulence model. The pressure distributions on the compression surfaces and in the air intake channel are obtained, the coefficients of the total pressure recovery and flow rate, the Mach number in the throat of the air intake are determined. The features of the flow structure for three variants of the air intake in the area of external compression are established: with side walls, side walls with slots and without side walls. The influence of the boundary layer bleed and lateral spreading on the launch and integral characteristics of a hypersonic air intake with a compact cross-section of the inner channel is determined. Satisfactory agreement between the calculated and experimental data is shown.