Turbulent oblique Shock Wave Boundary Layer Interactions (SBLIs) were investigated experimentally in two rectangular test section blow down-type supersonic wind tunnels, to examine three-dimensionality induced by the presence of side-walls, as well as the low frequency separation bubble breathing oscillation. Testing was performed at Mach 2.5 and 2, with incident shock deflection angles of \(8^{\circ }\) and \(12^{\circ }\) at the Cambridge University (UCAM) and TU Delft (TUD) supersonic wind tunnel facilities respectively. In the UCAM facility, Conical shaped artificial corner separation bodies were used to generate corner waves, similar to those produced by corner separations, and vary their location with respect to the primary interaction. This resulted in a wide range of separation geometries underneath the primary interaction. Correlations between the separation length and pressure rise through interaction along streamwise strips revealed a quasi-2D relationship. The separation length was primarily correlated with the pressure rise from separation to reattachment. A secondary relationship was observed between the separation length and the pressure rise induced upstream of the interaction by corner waves. Corner waves modify the pressure rise in the interaction and this can lead to a significant reduction/elimination of separation in some regions. This strong control authority of pressure waves on the separation length informed the design of shock control bumps. Separation-bubble-shaped shock control bumps were tested in both test facilities with the goal of reducing separation, and dampening the low frequency bubble breathing oscillation. It was shown that these bumps are capable of significantly reducing and even eliminating flow separation. They also significantly dampened/eliminated the low frequency oscillation.