Abstract
Prediction of flow field and thermal environment in the gap is crucial to the design of hypersonic vehicle thermal protection system. The compressible Navier-Stokes equation is solved to study the flow field and aerodynamic heating in the gap. The effect of inflow parameter on the aerodynamic heating is analyzed. The results show that there are vortex motions in the gap. The heat transfer in the gap mainly depends on the convection in the top region. The heat flux along the gap wall distributes in U-shape, and at the outlet of the gap is highest, which is the key point in the thermal protection design. As the angle of attack increases, the number of vortices will decrease gradually, and wall heat flux will increase, especially at the gap exit. The research results provide references for the design and optimization of thermal protection system.
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