Аннотация:Supersonic aerodynamic cooling effect implies adiabatic wall temperature decreasing in the wake of different obstacles like ribs, wedges or steps. This effect together with heat transfer enhancement in separated and reattached boundary layer can be utilized for higher efficiency of a new method of gas dynamic energy separation. This method is based on thermal interaction of subsonic and supersonic flows through a heat conducting wall resulting in heating of a supersonic flow and cooling of subsonic one.
