RÉSUMÉ

The results of numerical and experimental investigations of the specific features of supersonic air flow deceleration in convergent fixed-geometry inlets of various shapes with boundary layer control and air bypassing are reported. The inlets were designed to operate in a wide range of incoming flow parameters. Numerical simulations, based on solving the three-dimensional Navier–Stokes equations, were performed to compute the flow over the inlets in steady and throttling operation modes at M_∞ = 2−6. The experimental study was performed for models tested in the wind tunnels at TsAGI and CIAM at Mach numbers M_∞ = 2−5 and angles of attack α = 0°−7°. Reasonable agreement between the computed and experimental data is obtained.