Turbulent compressible boundary layer with heat-transfer effects on conditions at the sublayer

A theory for turbulent compressible boundary layer flow over a flat plate is presented, taking into account the effects of heat transfer on the conditions at the edge of the laminar sublayer. The skin friction equations are derived from the definition of boundary-layer momentum thickness and the momentum equation, from which von Karman's equation can be obtained for the incompressible case. Calculated skin friction coefficients in air are found to differ from the results of Van Driest (1956) by as much as 15% at Mach 11, demonstrating the importance of heat transfer effects at the sublayer. Skin friction measurements in helium at Mach 11.3 performed by Watson (1977) are shown to validate the present theory