Influence of Finite Width of Shock Generator on Shock-Wave/Boundary-Layer Interaction

What is it about?

There has been a growing demand for efficient long-range, high-speed supersonic passenger flights. When it comes to supersonic flights, the occurrence of shockwave boundary layer interaction (SBLI) is inevitable, and the repercussions are many. SBLI can occur in numerous aerodynamical instances, such as on the control surfaces of the aircraft, on transonic airfoils, in the nozzles at over-expanded conditions, the supersonic inlets, and many others. Current work focuses on the understanding the nature of the phenomenon which will help us in developing efficient geometries and novel control systems to alleviate the adverse effects of SBLI with separation.

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