Abstract: The viscous chemical reacting flow in the hydrogen-oxygen rocket engine chamber and nozzle is simulated by using loosely coupled point-implicit MacCormack scheme. In the numerical simulation the combustion process is modeled by using a 6-specis, 8-step finite-rate chemical reaction model, and the Baldwin-Lomax algebraic turbulent model is adopted. The distributions of flow parameters in the chamber and nozzle are presented. Analysis of the results show that the numerical simulation results are the same as the distributions of flow parameters in the hydrogen-oxygen rocket engine chamber and nozzle, so the result is proved to be reliable. The work of this paper lays a foundation for the numerical simulation of two-phase chemical reacting flow.