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Effect of Mass Flux Ratio above the Submerged Part of a Nozzle with a Contoured Inlet on the Discharge Coefficient

  • AIRCRAFT AND ROCKET ENGINE THEORY
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An Erratum to this article was published on 01 September 2020

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Abstract

The up-to-date methods of computational fluid dynamics (CFD) were employed to study the effect of mass flux ratio above the submerged part of a solid rocket engine nozzle with a contoured inlet on the discharge coefficient. The results are given in correlation with the inlet geometry and nozzle submergence.

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ACKNOWLEDGEMENTS

This work was supported by the Russian Foundation for Basic Research, grant no. 19-38-90277.

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Authors and Affiliations

  1. Tupolev Kazan State Technical University, ul. Karla Marksa 10, 420111, Kazan, Tatarstan, Russia

    A. N. Sabirzyanov & A. N. Kirillova

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  1. A. N. Sabirzyanov
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  2. A. N. Kirillova
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Correspondence to A. N. Sabirzyanov.

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Sabirzyanov, A.N., Kirillova, A.N. Effect of Mass Flux Ratio above the Submerged Part of a Nozzle with a Contoured Inlet on the Discharge Coefficient. Russ. Aeronaut. 63, 310–316 (2020). https://doi.org/10.3103/S1068799820020178

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