The influence of viscosity and turbulence on the supersonic flow compression and expansion corner

Super- and hypersonic flow around aircraft elements is accompanied by the formation of a complex structure, which characterized presence strong shock waves, rarefaction contact discontinuities, separation reattachment flow. For such problems, interaction waves with viscous boundary layers characteristic. Such quite largely determines effectiveness aircraft. When flowing structures their power plants in vicinity convex corner points geometry, compression expansion flows are locally realized. The calculation oblique formed when angle, simple angle expansion, included as an element solving many problems constructing streamlines finding pressure distribution on streamlined surface. Based technology adaptive meshes, numerical model proposed for studying two-dimensional effects arising from supersonic angles expansion. Numerical simulation was performed using various models inviscid, laminar or turbulent. In calculations, Mach number incident wave varies 2 to 15, 5 15 degrees. Reynolds number, calculated characteristics unperturbed flow, equal 105. working gas air (γ = 1.4). A qualitative picture during diffraction steps different geometry considered. interacts recirculation region observed, Prandtl–Mayer misaligned. results calculations compared theoretical data parameters behind front fan wave. Studies have shown influence viscosity turbulence structure can find application related design intakes high-speed flying aircrafts, particular, parametric optimization gas-dynamic that arise propulsion systems