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研究了简化模型超音速燃烧室流场和性能的数值模拟方法，该燃烧室在支板后缘设置一缝隙式喷嘴，平行于超音速空气流喷射氢气。用椭圆型偏微分方程数学模型，ＭａｃＣｏｒｍａｃｋ差分格式成功地计算了两种不同后绿尺寸的流场及其性能，为了对照比较，还计算了另外两种流场。计算结果表明，支板后的流场存在回流区，因喷氢的压力高于超音速空气流的压力和壁面附面层的影响，燃烧室内将出现斜冲波和膨胀波，压力沿横向变化明显，由此证明流场与“边界层流动”有性质上区别。提出了全流场按性质不同分段进行数值模拟的方法，利用计算得到的流场节点状态参数（如温度、压力等），积分获得燃烧室的性能参数，和文献的实验数据对比，计算结果合理、可靠。
A numerical simulation method for the flow field and performance of a simplified model supersonic combustor was studied. A slit nozzle was installed on the trailing edge of the supporter to inject hydrogen gas parallel to supersonic airflow. By using the mathematical model of elliptic partial differential equation and the MacCormack difference scheme, the flow field and its performance of two different green sizes were successfully calculated. For comparison, two other flow fields were calculated. The calculation results show that there is a recirculation zone in the flow field after the support plate. Because the pressure of hydrogen injection is higher than the pressure of the supersonic airflow and the influence of the wall surface coating, diagonal waves and expansion waves appear in the combustion chamber. The pressure changes along the lateral direction Obviously, it proves that the flow field is qualitatively different from “boundary layer flow”. A method for numerical simulation of full flow field by different segments was proposed. The performance parameters of the combustion chamber were obtained by integrating the calculated state parameters (such as temperature and pressure) of the flow field. Compared with the experimental data, the calculation results Reasonable and reliable.