An experimental study and analysis on complex shock wave/boundary layer interactive flows induced by protuberances at hypersonic speed

摘要

This complex separated flows induced by shock wave/turbulent boundary layerwere studied at Mach number of 5 experimentally. Two kinds of the cylinders as the obstacles mounded on the surface, which induced the different flowfields. Some analyses depend on the results from the measured static pressure distributions, the schlieren photographs and the oil flow patterns. And it shows the effects of the geometric shapes (leading edge and section form) and length scales on the classification of the interactive flowfield.