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 fl uid fl ow 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–ω model of turbulence. Data on the structure of the fl uid fl ow in such a channel with a narrowing inlet part and a next part of constant cross section, the limiting fl ow lines on the longitudinally ribbed lower surface of the channel, and the profi les of the velocity of the fl ow and the total pressure in the boundary layer in the channel have been obtained for the case where the Mach number of the fl uid fl ow incoming to the channel is M = 4.
Numerical investigations of the asymmetry of a fl uid fl ow 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–ω model of turbulence. Data on the structure of the fl uid fl ow in such a channel with a narrowing inlet part and a next part of constant cross section, the limiting fl ow lines on the longitudinally ribbed lower surface of the channel, and the profi les of the velocity of the fl ow and the total pressure in the boundary layer in the channel have been obtained for the case where the Mach number of the fl uid fl ow incoming to the channel is M = 4.
Author:  I. I. Mazhul′
Keywords:  numerical simulation, supersonic fl ow, rectangular channel, longitudinally ribbed surface.
Page:  999