自七十年代以来人们使用实验和CFD手段对固体火箭冲压发动机补燃室流场进行了不断的分析研究。本文简要介绍了实验概况和数值模拟所用的物理模型和计算方法,最后提及新近发展的耦合解法——块隐式法。 Since the 1970s, experiments and CFD methods have been used to analyze the flow field in the afterburner of solid rocket ramjet engines. This article gives a brief introduction of the experimental profiles and the physical models and computational methods used in numerical simulations. Finally, we discuss the newly developed coupling solution, the block implicit method.