The paper presents a physical-mathematical and computational model of the flow in a rocket engine nozzle. The combustion products of the fuel are simulated as a mixture of perfect gases, taking into account the dependence of the thermodynamic properties of the components on the temperature and pressure. To simulate the chemical equilibrium and nonequilibrium flows, a direct problem of the nozzle theory is solved. The results of comparison between the calculated and the reference data are provided.
One-Dimensional Model for Calculating Losses due to Chemical Nonequilibrium in a Rocket Engine Nozzle
Russ. Aeronaut.
Russian Aeronautics ; 67 , 3 ; 601-609
2024-09-01
9 pages
Article (Journal)
Electronic Resource
English
Nonequilibrium Rocket Nozzle Recombination Losses
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