An algorithm has been developed that makes it possible to calculate the reacting flows of combustion products in the nozzles of rocket engines. Calculations of the flow of combustion products of model fuel for a test configuration of a rocket engine with a radius-conical nozzle are carried out. Specific impulse losses due to chemical nonequilibrium in the gas phase are determined.
Перспективы развития фундаментальных наук : сборник научных трудов XVIII Международной конференции студентов, аспирантов и молодых ученых, 27–30 апреля 2021 г.. Томск, 2021. Т. 3 : Математика. С. 91-93