| Abstract: | The interaction between a boundary layer and a supersonic flow past a plate with a flap deflected at a small angle in the presence of strong cooling of the body surface is considered. For supercritical regimes, the entire interaction region is located behind the leading edge of the flap and the pressure distribution has a discontinuity of the derivative near the corner point. The flow in a break-point neighborhood with a characteristic length  x of the order of the boundary layer thickness is studied. It is shown that in this region a substantial pressure difference arises. The pressure distribution along the surface is found. The viscous sublayer in this region develops under the action of the given pressure gradient. |
