The prediction of Mach stem height can be important in the design of supersonic intake in supersonic and hypersonic flows. It is also important because of the progress in aircraft and rocket engines. An analytical method of predicting the Mach stem height is necessary in theoretical field of shock reflection and is the basis of the comparable computational fluid dynamics (CFD) method. A method for predicting the Mach stem height in steady flows is performed based on the earlier models. In this article, an analytical model for predicting the Mach stem height is improved based on two main assumptions: one is the calculation of the triple point deflection angle when the Mach stem is an oblique shock and the other is about the shape of the free part of the slip line. Under these assumptions, the relations predicting of Mach stem height in two-dimensional steady flow are derived based on the advanced averaging method of the subsonic flow region. The Mach stem heights are decided solely for the incoming flow Mach numbers and the wedge angles by the improved analytical model. As a result, the Mach stem heights by the model of this article are found to agree well with experimental results at lower Mach numbers, but there are relative errors at higher Mach numbers. The convexity of the slip line is also considered.

马赫杆高的预测对于超音速和高音速流中超音速进气口的设计可能很重要。由于飞机和火箭发动机的进步，这一点也很重要。在冲击反射的理论领域中，预测马赫杆高度的分析方法是必要的，并且是可比的计算流体动力学（CFD）方法的基础。基于较早的模型，执行了一种预测稳定流中马赫杆高的方法。在本文中，基于两个主要假设改进了用于预测马赫杆身高度的分析模型：一个是当马赫杆身是斜向冲击波时计算三点偏转角，另一个是关于自由零件的形状滑移线的 在这些假设下，基于亚音速流区域的高级平均方法，推导了二维稳流中马赫杆高的关系预测。马赫的阀杆高度仅由改进的分析模型确定，用于输入流量马赫数和楔角。结果，发现本文模型的马赫杆高与较低马赫数下的实验结果吻合良好，但在较高马赫数下存在相对误差。还考虑了滑移线的凸度。发现本文模型的马赫茎高与较低马赫数下的实验结果吻合良好，但在较高马赫数下存在相对误差。还考虑了滑移线的凸度。发现本文模型的马赫茎高与较低马赫数下的实验结果吻合良好，但在较高马赫数下存在相对误差。还考虑了滑移线的凸度。