| Abstract: | The present study is devoted to the computational investigation of the compressible turbulent boundary layer and flow that are formed during tangential blowing of various gases in a thick boundary layer for large positive pressure gradients. Such flows occur in elements of the gas-dynamic channel of turbojet engines and liquid-fuel rocket engines, ejector pumps, and other technical devices. Using a numerical method we investigate the effect of various factors (the Mach number of blowing, the type of blown gas, and the intensity of variation of the pressure gradient) on the stability of the boundary layer up to its separation. |
