This work continues the research on modeling the management regime in the boundary layer of compressible gas. The effect of the distribution of heat and mass transfer on the stability characteristics of supersonic boundary layer at high supersonic Mach number M = 5,35. The focus is on the modeling of acoustic disturbances in the conditions as a normal injection, in which the only nonzero component of the average velocity V, and the injection of other areas, including tangential, when the wall is not zero only U component. Production close to the problem of influence on the development of gas curtain small oscillations. It is assumed that the effect of injection of a homogeneous gas of different temperature similar to that of the blowing gas of different density, namely, blowing cold gas simulates heavy gas blowing and vice versa. Therefore in this modeling work is achieved by changing the factor of temperature (heating or cooling of the walls). The variant when the socalled regime implemented «lock» when the velocity perturbations on the porous surface can be taken as zero.
Influence of Heavy Gas Blowing into the Wall Layer of Supersonic Boundary-Layer on Its Transition