Direct numerical simulations of laminar shockwave boundary layer interactions were carried out for two Mach numbers, M=2.3 and M=5.92. For the smaller supersonic Mach number, the focus was on the effect of sweep on the flow similarity. Three sweep angles, 22.5, 40 and 53 deg, were considered. Simulations with unswept leading edge exhibit cylindrical similarity of the interaction region for 22.5 deg sweep and cylindrical symmetry otherwise. When the leading edge was swept, cylindrical similarity was obtained for all sweep angles. The focus of the simulations for the larger hypersonic Mach number was on the effect of sweep on stability. For these simulations periodic boundary condition were employed in the spanwise direction and the resulting data were analyzed with the proper orthogonal and dynamic mode decomposition. In accordance with Hildebrand et al., steady spanwise perturbations that grow in time inside the interaction region are observed for the unswept case. When a mild freestream crossflow component is added for a sweep angle of 10 deg, traveling oblique waves appear in the interaction region likely as a result of crossflow instability. A further increase of the sweep angle to 22.5 deg leads to the damping of all disturbances which suggests that sweep is ultimately stabilizing.
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