Marching method for calculating shock wave form in problems on supersonic inviscid flow past blunted bodies

New fast numerical iteration method is developed for ideal flow over supersonic flight body. It is based on the iterations over normal pressure deviation from local similarity pressure in the subsonic region of shock layer. The new hyperbolic approximation of Euler equations is deduced, providing pressure distribution with high accuracy. If we take this as initial approximation, one iteration is needed only. It is not required the form of shock wave to be given for numerical calculations. The form of shock wave is computed by marching method simultaneously with the other gasdynamic characteristics. This procedure is fitted to calculate the flow up to big values of azimuth angles. Algorithm is useful for computing flow fields in the whole range of Mach numbers, and fit as for outward so internal inviscid and viscous flows.