New formulations of the equations for compressible flow
Introduction. A prominent aerodynamic effect of combustion in a moving gas stream is an alteration of the flow pattern owing to heat release within the fluid. This alteration occurs not only in the immediate neighborhood of heat sources but also downstream where the entropy and stagnation temperature vary from one streamline to another. As a background for combustion research, appropriate descriptions of these altered flow patterns have been investigated. This paper considers the downstream patterns, which are restricted to be the adiabatic and steady flows of an inviscid fluid. In a second paper,1 diabatic (i.e., non-adiabatic) flows will be discussed. Since one-dimensional flow theory2,3 can be considerably condensed by use of the local Mach number M, it was natural to seek a corresponding condensation with the help of the Mach vector