Simulation of a Rocket Engine Nozzle Discharge Coefficient
- Авторы: Sabirzyanov A.N.1, Glazunov A.I.1, Kirillova A.N.1, Titov K.S.1
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Учреждения:
- Tupolev Kazan National Research Technical University
- Выпуск: Том 61, № 2 (2018)
- Страницы: 257-264
- Раздел: Aircraft and Rocket Engine Theory
- URL: https://journals.rcsi.science/1068-7998/article/view/230518
- DOI: https://doi.org/10.3103/S1068799818020150
- ID: 230518
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Аннотация
Multiparameter studies of the discharge coefficient dependence on the nozzle geometry and the presence of a condensed phase in combustion products were performed. The simulation results obtained satisfactorily agree with the well-known generalized data. The modern computational fluid dynamics methods were shown to be able to refine the generalized empirical relations.
Об авторах
A. Sabirzyanov
Tupolev Kazan National Research Technical University
Автор, ответственный за переписку.
Email: ANSabirzyanov@kai.ru
Россия, ul. Karla Marksa 10, Kazan, 420111
A. Glazunov
Tupolev Kazan National Research Technical University
Email: ANSabirzyanov@kai.ru
Россия, ul. Karla Marksa 10, Kazan, 420111
A. Kirillova
Tupolev Kazan National Research Technical University
Email: ANSabirzyanov@kai.ru
Россия, ul. Karla Marksa 10, Kazan, 420111
K. Titov
Tupolev Kazan National Research Technical University
Email: ANSabirzyanov@kai.ru
Россия, ul. Karla Marksa 10, Kazan, 420111
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