Heat-transfer and skin-friction measurements at a mach number of 2.44 for a turbulent boundary layer on a flat surface and in regions of separated flow

Abstract

A considerable body of data exists concerning the skin friction, the heat-transfer characteristics, and the wall temperature for zero heat transfer for turbulent boundary layers in supersonic flow in the absence of separation. Experiments have been made with bodies of revolution, flat plates, wind-tunnel walls, or with other arrangements Where the streamwise pressure gradient is zero the results can be approximately related to equivalent conditions on a flat plate. These 'equivalent flat plate' data are of great practical use, since the characteristics of turbulent boundary layers in most engineering applications (as, for example, in the flow over the wings of an aircraft), roughly approximate to those of a boundary layer on a flat plate. A comparison of the experimental findings for boundary layers at constant pressure suggests several general conclusions.