Different kinds of roughness appear on the nose of the hypersonic vehicle during the process of thermal destruction of thermal protection coating, which leads to earlier transition. Another important factor affecting the position of the laminar-turbulent transition is the bluntness of the nose or the leading edge of the vehicle. This factor shifts the transition downstream. Thus, the presence of a roughness on the blunted nose-tip of the vehicle creates an ambiguous situation: the stabilizing effect of bluntness competes with the destabilizing effect of roughness. Present work is a continuation of the work [1] and focused on the investigation of evolution of turbulent spots in the boundary layer.
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