Abstract: An experimental investigation was made for the shock wave/turbulent boundary-layer interactions induced by swept compression corners.The techniques used in this studywere the surface pressure distribution measurement and surface oil-film streak visualization.Effects of upstream Mach number M_∞ on the behavior of separation and the condition forincipient separation were mainly studied. The test Mach numbers were 1.79,2.04 and 2.50and the Reynolds numbers were about 2.42 2.47×10￣7/m。 15 compression corner mo...