Experimental Studies on Micro-Ramps at Mach 5

The performance of hypersonic propulsion can be critically affected by shock wave/boundary layer interactions (SBLIs), whose severe adverse pressure gradients can cause boundary layer separation. This phenomenon is very undesirable in engine intakes leading to total pressure loss and flow distortion which can cause engine unstart. Hence, it is essential to apply flow control method to the flow, either at the beginning or during the interaction phenomenon to prevent the shock-induced separation [1].