3D Shock/Boundary Layer Interaction on a Delta Wing With a Compression Ramp

This paper discusses an experimental study of a 3D shock/boundary layer interaction caused by various boundary layer states interacting with a highly swept delta wing with a trailing-edge compression ramp. A flat delta wing was also tested to explore boundary layer transition physics apart from the shock/boundary layer interaction itself. Experiments were conducted at Mach 6 in The Ohio State University Large Area Reflected Shock tunnel for unit Reynolds numbers ranging from 2.7 M/m to 8.6 M/m and wall temperature ratios (T