FLOW IN THE NEIGHBORHOOD OF THE BREAKPOINT OF THE LEADING EDGE THIN WING AT THE STRONG INTERACTION REGIME

摘要

The spatial laminar boundary layer on a thin wing in the neighborhood of the breakpoint of the leading edge in hypersonic wrap is investigated in this paper. The regime of strong viscous-inviscid interaction is considered. Variables, allowing for the reduction of the boundary value problem to a two-dimensional, and on the front edge, to systems of common differential equations are defined. To determine the induced pressure, the second-order differential equation is used. A numerical solution of the problem is obtained. The results of parametric calculations of the wing shape influence in plan, temperature factor, adiabatic exponent, and Prandtl number on the flow characteristics in the spatial boundary layer are presented. The size of the subsonic flow in a laminar boundary layer is also defined.