超燃冲压发动机流量匹配的临界流量法

为了使用基于积分方程的超燃冲压发动机性能计算模型模拟跨燃、亚燃工作模态，用临界流量法建立用于表征燃烧室热壅塞程度的残差方程，并以隔离段出口静压为独立变量，通过牛顿迭代法迭代求解残差方程，模拟了燃烧室内存在临界截面（即喉道）但不出现热壅塞的实际跨燃、亚燃工作状态。结果表明：该方法能够确定有喉道的超燃冲压发动机燃烧室一维参数分布，并具有计算精度高、计算速度快、收敛性好等优点，可以为基于积分方程的超燃冲压发动机性能计算模型求解提供一定的参考。

The Model Critical Mass Flow Method Based on Flow Matching of Scramjet

In order to simulate the transonic and subsonic modes using the scramjet engine performance computational model established by this research group which based on the integral equations, the residual equation is established by critical mass flow method with a independent variable of static pressure at the export of isolator in this paper. This equation which expresses the extent of thermal chock is iterated by Newton-Raphson method to simulate the working condition of the transonic and subsonic modes on which there is a critical cross-section and no thermal chocks, viz. a thermal throat, in the combustor. The results show that the distribution of one-dimension parameters with a thermal throat in the combustor can be simulated with this method. Meanwhile, this method is of high accuracy, fast computing speed and good convergence. It contributes much to the solving of the scramjet engine performance computational model.