Semenev

pp. 47-70

In this paper the authors present results of their numerical and experimental study of a supersonic separated flow and heat transfer in a flat channel with a sudden one-sided expansion at Mach number М ≈ 3 and with the presence of a turbulent boundary layer before separation. The numerical model was based on RANS (Reynolds Average Navier – Stokes Equations) with k-ω, k-ε and Spalart – Allmaras turbulence models. Computational fields of main gas-dynamic parameters in a stepped channel were also given. Comparison of numerical distributions with experimental data for wall pressure and heat-transfer coefficient downstream of a bench was carried out. A correlation analysis of the obtained velocity fields, wall pressure and friction, heat transfer coefficient in the area of separation and reattachment of turbulent boundary layer was also conducted.