Development of experimental and computational system for investigation of film-cooling effectiveness liquid rocket engine of small thrust
Aerospace propulsion engineering
Аuthors*, **, ***
Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia
AbstractThe technical article about problem of development method optimal mass flow rate determination of film-cooling LRE small thrust. It describes ways of cooling the walls of the chamber and nozzle rocket engine, and an algorithm for the development of LRE of small thrust with using experimental and computational systems.
Keywords:LRE of small thrust, film-cooling effectiveness, experimental and computational system.