Abstract
A review of experimental and numerical studies of the interaction of oblique shock waves with boundary and entropy layers of the blunted plate, performed by the authors, is presented. Three variants of interference flow were studied, namely, a shock wave impinging on a plate from the outside, the flow near a sharp wedge mounted on a plate, and the flow near a pair of counter wedges mounted on a plate. The strong influence of even small plate bluntness on the flow structure and heat transfer at hypersonic flow velocities is revealed. The influence of the basic gas-dynamic parameters and geometrical characteristics of the investigated structures on the nature of the interference flow and the maximum value of the heat transfer coefficient is studied. The experiments were carried out in the UT-1M shock wind tunnel at Mach numbers M∞ = 5–10 for a wide range of Reynolds numbers and laminar and turbulent states of the undisturbed boundary layer. In addition to discrete sensors, panoramic methods for heat flux and pressure measuring were widely used. For numerical simulation of the flow, the Reynolds-averaged Navier–Stokes equations were solved using the q-ω turbulence model.
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