Author: Allan R. Wieting

Publisher:

Published: 1987

Total Pages: 282

ISBN-13:

An experimental study of shock wave interference heating on a cylindrical leading edge representative of the cowl of a rectangular hypersonic engine inlet at Mach numbers of 6.3, 6.5, and 8.0 is presented. The primary goal of this study was to obtain a fundamental understanding of the fluid mechanics of shock wave interference induced flow impingement on a cylindrical leading edge and the attendant surface pressure and heat flux distributions. The study has provided the first detailed heat transfer rate and pressure distributions for two-dimensional shock wave interference on a cylinder along with insight into the effects of specific heat variation with temperature on the phenomena.