Large-eddy simulations of an impinging shock interacting with a turbulent boundary layer are performed at free-stream Mach number M_∞ = 7.4 and several shock angles at two cooled wall conditions (wall-to-recovery temperature ratio of T_w/T_r = 0.33 and T_w/T_r = 0.13), both representative of experiments from the German Aerospace Center (DLR). The objective of this study is (ⅰ) to perform preliminary LES to study the effect of the wall thermal condition on SBLI in the hypersonic regime; and (ⅱ) to assist in the design of the new hypersonic shock/boundary-layer interaction experiment carried out at DLR.
展开▼
