Control of Shockwave Boundary Layer Interaction using Plasma-Assisted Shock Control Bump

The shockwave boundary layer interaction (SWBLI) is a key phenomenon in high-speed flows. Many attempts, active and passive, have been made to manipulate SWBLI. Shock control bumps (SCBs) are passive flow control devices that have shown control authority in transonic and supersonic applications. At on-design conditions, SCBs reduce wave drag significantly, while increasing viscous drag slightly. However, at off-design conditions, the SCB promotes boundary layer thickening which drastically increases viscous drag and causes boundary layer separation. A combination of two-dimensional SCBs with plasma actuators is proposed to address the off-design limitations of SCBs when used alone. Dielectric barrier discharge (DBD) actuators driven by nanosecond repetitively pulsed (NRP) plasmas will be imbedded in the surface upstream of the SCBs to perturb the impinging shock. The control authority of the combined plasma actuators and SCBs will be assessed in Mach 2 flow using characterization of the base flow and controlled flow by streamwise pressure measurements and schlieren visualization.