Numerical analysis of two-dimensional problem of supersonic shock wave interaction with a boundary layer
The results of numeric modeling of the nature of supersonic turbulent flows interaction in the field of inclined from the windward side plane of the step for the canting angle β = 8, 25, 90° and Mach numbers M∞ = 2,9, 2,94. The Navier-Stokes equations averaged by Reynolds with the usage of turbulent model were used as a mathematical model k-ω SST for viscous compressed environment. Comparative analysis of the pressure distribution and surface friction with gained experimental data was held.