Aeroelastic Effects in Supersonic Shock-Turbulent Boundary Layer Interaction over Flexible Panels

What is it about?

The study looked at how an oblique supersonic shock wave interacts with a flexible panel compared to a rigid one. High-resolution simulations and wind tunnel experiments are used to examine how the flexible panel and impinging shock wave affect each other. The results show that the flexible panel's unsteady motion changes the size and location of the high-pressure region caused by the impinging shock wave, which in turn affects the flexible panel bending. More specifically, the study reveals that the interaction between the resulting bending of the flexible panel and the impinging shock wave is more strongly coupled at the first (dominant) mode but less so at the secondary modes.

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