Abstract: | We performed a numerical study of the boundary layer on a wall in a supersonic gas flow using a differential turbulence model. The dependences of the recovery factor and the Reynolds analogy factor on the main flow parameters, such as the Reynolds, Mach, and Prandtl numbers, are obtained for a series of the temperature factor values. The results of calculations are approximated by the dependences of the recovery factor and the Reynolds analogy factor on the Prandtl number. |