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Aspects of the numerical method calculating thermogazodynamic lrest based on not perfect passing of workflows in the combustion chamber
- Authors: Silyutin M.V.1, Shustov S.A.1
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Affiliations:
- Samara State Aerospace University named after academician S.P. Korolyov (National Research University)
- Issue: Vol 10, No 3-4 (2011): Special Issue
- Pages: 71-77
- Section: AIRCRAFT AND SPACE ROCKET ENGINEERING
- URL: https://journals.ssau.ru/vestnik/article/view/6935
- DOI: https://doi.org/10.18287/2541-7533-2011-0-3-4(27)-71-77
- ID: 6935
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Abstract
Are stated results of using methodic of numerical thermogasdynamic calculating of rocket engine of small thrust (LREST) with account of not the ideal course of workflows in the combustion chamber.
About the authors
M. V. Silyutin
Samara State Aerospace University named after academician S.P. Korolyov (National Research University)
Author for correspondence.
Email: tdla@ssau.ru
assistant of department theory of aircraft engine
Russian FederationS. A. Shustov
Samara State Aerospace University named after academician S.P. Korolyov (National Research University)
Email: tdla@ssau.ru
Candidate of technical Sciences
associate Professor of theory of aircraft engine department
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