On one particular solution of the problem of spatial hypersonic flow past a variable form thin wing

The work is dedicated to the further study of the hypersonic gas flow past a thin wing problem. The wing shape depends on the time. The resulting head shock wave is attached to the front edge of the wing, at least at one point. The solution is constructed using the thin shock layer method.. In determining the first order corrections two equations resulting system can be integrated independently of the others. Introduction of a new function and application of the Euler-Ampere transformation allows us to build a solution that depends on two arbitrary functions and unknown forms the front of the head shock wave. To determine these functions obtained integro-differential system of equations. In this paper we present one of variants of the semi-inverse method of constructing a solution in which a type of one of arbitrary functions is given. The shape of the streamlined body is defined in the process of constructing the solution of the problem. A particular solution of integrodifferential equations of the system is built, The formulas for determining the shape of the shock front, the body surface, the distance between the shock wave and the body surface, the flow parameters on the wing surface were obtained.