shock boundary layer interactions

Investigating the effects of non-adiabatic walls on shock/boundary-layer interaction at low reynolds number using direct numerical simulations

Direct numerical simulations are employed to investigate the flow properties of a shock wave interacting with a turbulent boundary layer at free-stream Mach number M∞ = 2.28 with distinct wall thermal conditions. Adiabatic, heating and cooling wall conditions are considered for a wide range of deflection angles. While heating contributes to increase the extent of the interaction zone, wall cooling turns out to be a good candidate for flow control.

Using large-eddy simulations to design a new hypersonic shock/boundary-layer interaction experiment

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 Tw/Tr = 0.33 and Tw/Tr = 0.13), both representative of experiments from the German Aerospace Center (DLR).