Abstract
A new computer program has been written to calculate the properties of the recirculating base flow region of a rocket exhaust plume. The nozzle stream and the freestream, either of which may be supersonic, mix turbulently to form an axisymmetric compressible free boundary layer. Solutions of the elliptic differential equations, which incorporate a two-equation model of turbulence closure, are obtained using an iterative finite-difference technique coupled to a point-by-point solution of the chemical kinetics. Predictions are presented for the velocity, pressure, temperature, and species concentration distributions in the base recirculation region of a rocket exhaust plume under supersonic flight conditions.
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