Turbulent boundary-layer studies at high Reynolds numbers at mach numbers between 0.2 and 2.8

Abstract

Measurements of the turbulent boundary layer on the sidewall of the RAE 8ft x 8ft wind tunnel are described. The measurements consisted of surface shearing stress, using a large strain-gauge balance, together with velocity and temperature profiles. Maximum Reynolds numbers, based on an effective streamwise run, range from about 200 million at M = 0.2 to 60 million at M = 2.8. The analysis of the results shows that accepted descriptions of turbulent boundary layers in incompressible flow, derived from the concept of a universal velocity defect law, are preserved for compressible flows if the boundary-layer parameters are expressed in kinematic form. This leads to a simple method of calculating skin friction and velocity profiles for constant pressure flows without heat transfer.