Shock-Wave/Boundary-Layer Interactions on an Axisymmetric Body at Mach 2

What is it about?

Shock wave boundary layer interactions (SBLI) are a rudimentary occurrence in supersonic flow that are induced by the convergence of a shock wave and a boundary layer on a solid surface. As the growing desire for sustained supersonic/hypersonic flight continues to drive the motivation behind this long studied flow phenomenon, it is imperative that mysteries behind its complex nature are uncovered. The present experimental study investigates the flow field resulting from the impingement of a planar oblique shock on an axisymmetric body with an aim to characterize its global flow features and SBLI.

Featured Image