Abstract
Issues of numerical modeling of spatial gas dynamics and heat exchange in the back lip cavity of the combustion chamber of a large solid-propellant rocket motor (SRM) are considered. Topological features of the flow structure and thermophysical parameters near the nozzle cap in the back lip cavity are analyzed. Distribution of the heat transfer coefficient over the nozzle bottom surface in the back lip cavity is obtained by the radial coordinate. The obtained dependences fairly correlate with the known experimental data.
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