Studies of the turbulent boundary layer on a waisted body of revolution in subsonic and supersonic flow

Abstract

Summary. The object of the study was to determine the influence of Mach number, pressure gradients and streamline convergence and divergence on the development of turbulent boundary layers. Measurements were made of pressure distribution, local skin friction and boundary-layer profiles along the body, at Mach numbers between 0.6 and 2.8 and Reynolds numbers, based on the length of the body, between 5 x 10(to the power of 6) and 2 x 10(to the power of 7). The results of comparative calculations based on simultaneous integration of the momentum and kinetic energy equations are generally in fair agreement with the experiments except at the two higher Mach numbers (2.4 and 2.8). The study was a result of collaboration between the Aerodynamische Versuchsanstalt, Göttingen and the Royal Aircraft Establishment, Bedford.