An approach to solution of spatial hypersonic flow past a thin wing problem

The spatial hypersonic problem of the flow past a thin wing is studied. The head shock wave is attached to the wing leading edge, at least, at one point. The thin shock layer method and the Euler-Amper transformation are applied to the problem under consideration. For the first-order corrections, the system of differential equations is reduced to the integro-differential system of equations in order to determine two arbitrary functions and the form of the shock front. The system particular solutions are constructed. This approach provides the flow parameters to be presented in the final or integral forms.