Physical insight into a Mach 7.2 compression corner flow

摘要: High-order implicit Large Eddy Simulations were conducted to study shock-boundary layer interaction around a 33° compression corner at Mach 7.2 and Reynolds number of Reθ = 3,500 based on the momentum thickness. A grid-convergence was performed reduce computational uncertainty results compared with experiments theoretical predictions. Furthermore, turbulent flow properties analysed respect normal stress, skewness flatness, conclusions drawn regarding shock boundary behavior.