Axisymmetric Hows with given shock waves

Examples showing the possibilities to compute axisymmetric flow elements resulting from given shock waves arc given in (101}. The well known flow past a circular cone in supersonic flow is verified as well as generalizations for curved shocks w ith varying strength followed by rotational flow. Figure 5 illustrates the solution for a cone flow and for the flow past a curved axisymmetric shock wave element, as it occurs in the flow past an ogive body nose. The character! sties gnd depicts the full solution extending beyond the contour streamline: a limiting cone is found with no solution appearing near the cone axis.

This fast numerical method of characteristics is an inverse Euler solver to design 2D and axisymmetric flows with given shock waves. The flow past a circular cone has been described by Taylor and Maccoll. its conicity reduces this special case of axisymmetric flow to solving one ordinary differential equation This will be used in the following description of practical design methods by locally applying conical flow as an ‘osculating flow pattern’ in more general 3D boundary conditions. Curved shocks will allow for an even wider variety of using an axisymmetric flow element for 3D flow design.