A direct numerical simulation study is performed on the hypersonic shock wave/boundary layer interaction controlled by using a microramp vortex generator (MVG). The mean structures around the microramp generator are obtained and the comparison on the shock structures and surface flow patterns is made between cases with and without the MVG. The evolution of the vortical structures in the wake of the MVG is described and the evolution process is found to be similar to that in a supersonic flow. The detailed three-dimensional voritcal structures are presented. Furthermore, the effects of the MVG on the shock wave/boundary layer interaction are investigated. The results show that the heat flux and friction after the interaction have been reduced apparently by the MVG. Such reduction is mainly caused by the flow pattern near the reattachment and the alteration of the vortical structures after the interaction.
The prediction of heat transfer for blunt bodies in hypersonic flows remains a great challenge. In particular, the uncertainties are larger in the leeside due to the complexity of the wake flow. Generally, the heat transfer is over-predicted using the Reynolds-averaged Navier–Stokes (RANS) models. In this paper, the improved delayed detached eddy simulation (IDDES) method is used to simulate the Mach 6 flow around a scaled spherical capsule model. In addition, a low dissipative WENO scheme is used for inviscid fluxes and dual-time stepping method is applied for time advancement. Results are compared to experimental data for mean and instantaneous heat transfer in the leeside of the aftbody. It is shown that the integrated error is 75.49% for RANS while 35.69% for IDDES method. Moreover, the multi-scale structures in the separation region are also resolved well by the IDDES method.
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