A numerical simulation of the hydrodynamic effects arising in the process of work of the vectorable thrust nozzle of a solid-propellant rocket engine has been performed. The fields of the flows of combustion products in the channel of a charge, the prenozzle space, and the nozzle unit were calculated for different angles of vectoring of the nozzle. The distributions of the gasdynamic parameters of the flow of combustion products in the prenozzle space, corresponding to their efflux from the cylindrical and star-shaped channels of charges, were compared. The formation of a vortex flow in the neighborhood of the back cover of the nozzle was considered.
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Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 89, No. 3, pp. 652–661, May–June, 2016.
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Volkov, K.N., Emel’yanov, V.N. & Denisikhin, S.V. Formation of Vortex Structures in the Prenozzle Space of an Engine with a Vectorable Thrust Nozzle. J Eng Phys Thermophy 89, 660–670 (2016). https://doi.org/10.1007/s10891-016-1424-6
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DOI: https://doi.org/10.1007/s10891-016-1424-6