A Generalized method for the calculation of supersonic and hypersonic flow behind curved shock waves.

A method of calculating the performance of a hypersonic air intake has been developed. The method is based on the equilibrium flow of a calorically imperfect gas. It is applicable to both axisymmetric and two-dimensional surfaces, the shape of which can be specified by a sixth order polynomial. The method is applicable to both blunt and sharp leading edges. Boundary layer calculations are included. [...