Numerical simulation of chemical reacting flow in H₂/O₂ rocket engine thrust chamber

The viscous chemical reacting flow in the hydrogen-oxygen rocket engine chamber and nozzle was simulated numerically by using loosely coupled point-implicit MacCormack scheme. The chemical reaction model with six-species and eight-step finite-rate, and the Baldwin-Lomax algebraic turbulent model were adopted. The distributions of flow parameters in the chamber and nozzle were obtained. The analysis of the simulated results has shown that it is in agreement with the results of theoretical analysis, so the method of the numerical simulation has proved to be effective.