The nonstationary problem of finding the parameters of the hypersonic gas stream beyond the front of the head shock wave resulting in flowing a thin wing with a variable form has been considered. The problem has been solved by means of the thin shock layer method. The gas flow in the shock layer has been described by the set of differential equations of gas dynamics with the boundary conditions on the head shock wave front and the wing surface. It has been assumed that the head shock wave has been joined to the front edge of the wing, and the attack angle has been not small. The corrections to a pressure, a longitudinal vector velocity component and an enthalpy have been obtained on the basis of solving the integrodifferential equations set.