To　solve　the　viscous　chemical　reacting　flow　governing　equations　in　the　species　of　hydrazine　fuel　rocket　engine　thrust　chamber,　MacCormak　two-step　difference　scheme　with　coupled-implicit　method　combined　with　the　k-ε　turbulence　model　was　applied.　In　chemical　reaction　model,　there　were　17　species　and　12　limit　speed　chemical　reactions.　The　results　agree　well　with　the　theoretical　analysis.　Finally,　numerical　simulation　is　validated　by　experiment.　The　results　are　useful　and　important　to　the　design,　performance　improvement　and　theoretical　exploration　for　rocket　motor.