Wall temperature effects on shock unsteadiness in a reattaching compressible turbulent shear layer

In this study, the effect of heat transfer on compressible turbulent shear layer and shockwave interaction in a scramjet has been investigated. To end, highly resolved Large Eddy Simulations (LES) are performed to explore wall thermal conditions behavior reattaching free interacting with an oblique shock flows. Various wall-to-recovery temperature ratios considered, results compared adiabatic wall. It is found that affects reattachment location region. Furthermore, fluctuating flux exhibits strong intermittent severe mean, characterized by scattered spots. The distribution Stanton number shows complex pattern within interaction, maximum (heat rates) dynamic loads (root-mean-square pressure) for case cold analysis LES data reveals boundary condition can significantly impact pressure fluctuations level. primary mechanism changes flow unsteadiness due linked layer, which agrees theory.