Effect of the temperature drop between the isothermic walls of a channel on the structure of supersonic flow and on the aerodynamic properties

The results of numerical analysis of the two-dimensional Navier-Stokes equations are used to investigate a supersonic flow of a perfect gas in a symmetric plane channel of variable cross section at the Mach number of $\mathrm{M}_\infty=4$ at the inlet for the Reynolds numbers in the range $\mathrm{Re}=10^3-10^6$. The top and bottom channel walls are assumed to be isothermic with different values of the temperature factor. It is shown that the asymmetry of the boundary conditions for temperature leads to the asymmetry of the entire flow field.