Hypersonic shock–wave turbulent boundary-layer interaction over an axisymmetric curved compression ramp

The research activity is focused on the investigation of hypersonic shock–wave / turbulent boundary layer interaction (SWBLI) over an axisymmetric curved compression ramp. The project aims to analyze flow separation and reattachment phenomena, pressure gradients, and the turbulence structures induced by the interaction. The study will be carried out using an in-house numerical solver based on high-order schemes for the solution of the compressible, multicomponent Navier–Stokes equations. The objective is to advance the understanding of the underlying physical mechanisms on complex geometries and to contribute to the development of predictive models for hypersonic aerospace applications.