Three-dimensional supersonic flow past blunt bodies with contour discontinuities, with account for equilibrium and frozen state of the gas in the shock layer

Abstract

An algorithm is devised for calculating by the finite difference method the supersonic flow region for three-dimensional steady-state flow of a viscous gas past a blunted body with many contour discontinuities. The state of this gas at high hypersonic flight speeds can be characterized by equilibrium or frozen physicochemical processes.