Asymmetry of a Flow Which is Due to the Interaction of a Compression Shock with the Boundary Layer on a Longitudinally Ribbed Surface

Numerical investigations of the asymmetry of a fluid flow in the channel of an air intake which is due to the interaction of a compression shock, generated by the shell ring of the air-intake channel, with the boundary layer on the longitudinally ribbed lower surface of this channel have been performed on the basis of the Reynolds-averaged Navier-Stokes equations and the SST k-& omega; model of turbulence. Data on the structure of the fluid flow in such a channel with a narrowing inlet part and a next part of constant cross section, the limiting flow lines on the longitudinally ribbed lower surface of the channel, and the profiles of the velocity of the flow and the total pressure in the boundary layer in the channel have been obtained for the case where the Mach number of the fluid flow incoming to the channel is M = 4.