Numerical simulation of C-H-O-N system liquid rocket engine nozzle flow

The viscous flow in the C-H-O-N system liquid rocket engine nozzle was simulated by using the loosely coupled point-implicit MacCormack scheme. The reacting model and non-reacting model were used in the simulation, and a 12-species, 14-steps finite-rate chemical reaction model was adopted in the C-H-O-N reacting model. The distribution of low parameters in the nozzle were presented. The analysis of the results shows that the numerical simulation results are in accordance with the theoretical distribution of flow parameters in the nozzle. The numerical results provide a reference for the design and experiment of the rocket engine.