Experimental Investigation of Shock Wave Interaction With Various Boundary Layer Configurations

In this study, experiments are carried on different boundary layer structures, using Schlieren techniques, Particle Image Velocimetry (PIV), Pressure taps and optical sensors. The tests are performed in a supersonic wind tunnel on an elliptic flat-plate leading edge with finite thickness, a sharp flat-plate leading edge with finite thickness and a cone attached to a circular cylinder, all the tests are carried in a Mach 2 freestream flow where the shock is generated. The shock wave boundary layer interaction (SWBLI) is studied in terms of the interaction behavior. The primary goal is to investigate flow characteristics upstream, downstream, and at the shock-induced separation, the shock position, the collected pressure data and the frequency distributions of each structure, and this is to identify the flow pattern of each boundary layer and to study how geometrical modifications influence the flow as well as the SWBLI. The flow is visualized using a Schlieren imaging system and the images captured are investigated using optical sensors that are proposed to make turbulence measurements. Boundary layer characteristics are presented through experimental results.