Ricerc@Sapienza

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.

Direct numerical simulations are employed to investigate a shock wave impinging on a turbulent boundary layer at free-stream Mach number M=2.28 with different wall thermal conditions, including adiabatic, cooled, and heated, for a wide range of deflection angles. It is found that the thermal boundary condition at the wall has a large effect on the size of the interaction region and on the level of pressure fluctuations.