Abstract
Elements of a homogeneous algorithm for numerical simulation of the thermogasdynamic parameters of a viscous two-phase nonequilibrium chemically reactive nonisobaric rocket-engine exhaust jet have been formulated within the framework of a two-velocity and two-temperature continuum model on the basis of “viscous-layer” and “narrow-channel” equations. By numerical calculation, the authors has established the basic regularities of the influence of the water feed, the mixing of the jet with air, and the afterburning of the high-temperature rocket-engine jet in the air oxygen on the flow structure and thermogasdynamic and thermophysical parameters of the jet.
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