Abstract:
Summary. This report gives further experimental results for compressible turbulent boundary layers with air injection. The experimental arrangement is similar to that used by Jeromin (R. & M. 3526) but, by a slight modification of the injection equipment, and by a reduction in Reynolds number, it has been possible to obtain a threefold increase in injection rate at a Mach number of 2.5. Results were also obtained for a Mach number of 1.8. The basic velocity profiles are included in tabular form together with some of Jeromin\\'s results for a Mach number of 3.6. The present results, together with results for incompressible flow, have been used to study the law of the wall, the velocity defect law, and the eddy viscosity variation through the layer.
