Supersonic Turbulent Boundary Layer in Adverse Pressure Gradient. Part 11: Data Analysis

Abstract

Experimental measurements of the mean profile characteristics of the supersonic turbulent boundary layer in a moderate adverse pressure gradient are analyzed. Turbulent boundary-layer equations applicable to compressible flow over a surface with longitudinal curvature are evaluated by numerical integration using the tabulated profile data. Curvature corrections to the equation for conservation of streamwise momentum are shown to be small but of the same order of magnitude as the wall shear stress. The data are shown to correlate in law of the wall dimentionless coordinates using an integral compressibility transformation that follows directly from Prandtl's mixing length approximation of the Reynolds stress. Values of skin-friction coefficient determined using the experimental data are compared to other experimental data and to values predicted using the Spalding-Chi method.