Experimental Investigation of Shock-Wave–Streamwise-Vortex Interaction

What is it about?

The large-scale streamwise vortex structure present in the internal flow of an inward-turning inlet-isolator poses a critical aerodynamic challenge during hypersonic engine development. This study accordingly focused on the dominant phenomena in the flow field of an inward-turning inlet-isolator, observed the common issue of shock wave–streamwise vortex interactions in a concave channel, designed a series of experimental conditions, and conducted experiments using a wind tunnel with synchronized high-speed schlieren visualization and high-frequency wall static pressure measurements.

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