HEAT TRANSFER AND SKIN FRICTION FOR TURBULENT BOUNDARY LAYERS ON HEATED OR COOLED SURFACES AT HIGH SPEEDS

摘要

The method presented in NACA TN 2692 for evaluating the skin fric-tion of a turbulent boundary layer in compressible flow on an insulated surface is extended to evaluate the turbulent skin friction and heat transfer in compressible flow on a surface which is heated or cooled.nThe results of this analysis are in good agreement with the heat transfers measured in flight on the NACA RM-10 missile up to Mach num¬bers of 3.7.