Reynolds Analogy Coefficient in a Compressible Turbulent Boundary Layer with a Pressure Gradient

Numerical study of a compressible turbulent boundary layer in supersonic flow with adverse and favorable pressure gradients is carried out using the three-parameter differential RANS turbulence model. The pressure gradients are implemented by changing the Mach number of the free-stream flow along the plate. The study is carried out for a number of the free-stream Mach numbers (from 1 to 3) and two values of the temperature factor (0.5 and 1.5). Using the results of calculations of the flow and heat transfer characteristics, the dependences of the Reynolds analogy coefficient on two pressure gradient parameters are obtained.