Heat flux prediction for hypersonic flows using a stabilized formulation

This work focuses on the heat flux prediction in hypersonic flow regimes using the finite-element based Streamline-Upwind Petrov-Galerkin formulation enhanced with a discontinuity-capturing operator and weak enforcement of the Dirichlet bound-ary condition. The numerical formulation is validated on several benchmark cases including Mach 14 compression corner at 15 degrees and 24 degrees, 2D Mach 17 cylinder and 3D Mars Pathfinder re-entry vehicle at Mach 14. The numerical results are in very good agreement with the experiments or data available in the literature, showing the robustness of the numerical framework. Moreover, the newly proposed weak imposition of the no-slip boundary condition at the surface shows great potential for near-wall modeling of high-speed compressible flows.