Design Method for Axis-Symmetrical Gas Flow near Supersonic Aircraft Nose Tip

A method is suggested for calculating gas-dynamic parameters in shock layer in the process of supersonic flow around axis-symmetrical bodies at zero incidence. An algorithm has been developed on this basis to integrate Euler equations along the flow line (surface of the bodies). The algorithm combines the simplicity and on-line possibility of approximation approaches and may be compared in respect to precision with strict methods of calculation of shock layer parameters and shock wave shape.