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Abstract
A model for predicting physical characteristics of combustion in the recirculating, chemically-reacting flow in the base region of a rocket exhaust plume is described. The nozzle jet and the free stream are considered as supersonic or subsonic, mixing turbulently to form an axisymmetric and compressible free-boundary layer. The turbulence is accounted for by a two-equation model, which solves the transport equations for the local kinetic energy of the fluctuating motion and its dissipation rate. Full account is taken of heat-transfer effects, and a detailed finite-rate chemical-kinetics scheme is included, which allows for any number of species. Simultaneous solutions of the elliptic differential equations are obtained by a finite-difference technique, and the chemical-kinetic equations are solved by a procedure developed by Pratt and Wormeck (1976). The prediction procedure, composed of the mathematical model and its solution algorithm, is applied to predict the helds of variables for representative supersonic-missile flight conditions, with subsonic recirculating base-flow, and a full description of the chemistry. The results are presented and discussed.