Stagnation enthalpy effects on a hypersonic turbulent compression corner flow

Very high gas temperatures, which activate several thermochemical processes, are a typical feature of hypersonic flows. In this study, we investigate the effects of stagnation enthalpy on a turbulent boundary layer that flows over a cold isothermal compression corner. The analysis is carried out numerically by performing direct numerical simulations with the Hypersonic Task-based Research (HTR) solver (Di Renzo et al., Comp. Phys. Comm. 255, 2020). The main parameters of this fundamental configuration, including free-stream Mach number, wall-cooling, and free-stream stagnation enthalpy, are varied systematically in several calculations to highlight the response of the flow field. Moreover, both calorically perfect and imperfect gas models are taken into account in the mathematical formulation of the problem to highlight the effects of vibrational excitation on the flow dynamics. The variations of the skin-friction coefficient, wall heat flux, Reynolds analogy factor, and pressure fluctuations will be described in this talk while highlighting the importance of high-temperature effects on hypersonic turbulence.