Aspects of the numerical method calculating thermogazodynamic lrest based on not perfect passing of workflows in the combustion chamber

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 Federation

S. 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

Russian Federation

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