高超声速气动加热关联方法的适应性分析

针对高超声速飞行器热环境预测上有着重要应用的关联方法缺乏构造机制和适应性分析的问题，从驻点热流的Kemp-Riddell公式出发，推导了驻点斯坦顿数和雷诺数之间的经典关联关系，从理论上分析了上述关系的适应性。结果显示斯坦顿数和雷诺数关联关系受马赫数的制约，飞行条件和试验条件马赫数变化范围较大的情况下，更适合采用雷诺数和马赫数的组合变量开展关联分析。当试验来流静焓较低的情况下，过低静焓对热环境的关联特性有不利影响，需要提高试验来流马赫数，远离临界马赫数确保地面数据同飞行条件之间的关联性。在国内4座风洞上开展的风洞试验和DSMC/CFD的数值仿真分析工作，校验了上述结论在连续流区域的正确性。

Suitability Analysis on Correlation Relation of Aerothermodynamics Entry Environment for Hypersonic Flying Vehicles

 The correlation relation is the credible method to predict the entry aerothermodynamics environment to avoid the deficiency for a wind tunnel experiment and numerical method in hypersonic vehicle design. In this paper, the suitability for the classical Stanton number-Reynolds number correlation relation is researched theoretically, which is deducted from the Kemp-Riddell formula at the stagnation point. The results show that the Stanton number-Reynolds number correlation relation is not universal and restricted with the Mach number, and the Stanton number-combination variable of Reynolds number and Mach number is more universal to correlate the wind tunnel and flight condition. Too low static enthalpy condition for a wind tunnel experiment will harm the correlation relation, which requires enhancing the inflow Mach number to compensate. Then several experiments are carried on 4 wind tunnels, several simulation results are also provided from several teams. The results validate the new correlation relation.