In the present work, a method of mathematical simulation is employed to describe processes occurring in the specimens of new equipment and using the remaining propellant in rocket-engine tanks. Within the framework of certain turbulence models, the authors perform a calculation of the flow field in the volume of the tank of the launch-vehicle stage when a hot gas jet is injected into it. A vortex flow structure is revealed; the characteristics of heat transfer for different angles of injection of the jet are determined. The obtained correlation Nu = Nu(Re) satisfactorily describes experimental data.
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Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 91, No. 2, pp. 345–352, March–April, 2018.
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Fedorov, A.V., Bedarev, I.A., Lavruk, S.A. et al. Determination of the Flow Field in the Propellant Tank of a Rocket Engine on Completion of the Mission. J Eng Phys Thermophy 91, 324–331 (2018). https://doi.org/10.1007/s10891-018-1752-9
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DOI: https://doi.org/10.1007/s10891-018-1752-9