Integral Method for Uniform Calculation of Subsonic and Supersonic Regions in a Plane and Axisymmetrical Hypersonic Flow.

The solution of the direct problem is found by using a uniformly valid, analytic, approximate solution of the inverse problem for nonviscous hypersonic flow. Velocity and density are assumed to have linear dependence on the stream function. Then the formulation of the direct problem leads to a system of ordinary differential equations in tengential direction. the use of the stream function in the linear expressions for velocity and density has the advantage that this system of differential equations can be used in thwhole flow field, that means in the local subsonic and the supersonic regions. An iterative procedure similar to the Dorodnitsyn method is employed to solve it numerically. Numerical results are given and discussed for ideal gases with constant specific heats.