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中文摘要：
运用快速算法对高超声速飞行器外表面的一些关键部位经受的气动热环境进行计算分析。在理论和经验公式的基础上，利用轴对称比拟法考虑攻角影响，采用局部相似性解及参考焓等方法确定飞行器有攻角再入的表面气动加热，发展了一套高超声速飞行器关键部位气动热的计算方法。以钝锥为算例对计算方法进行了验证，结果表明，本文所述方法具有较高的效率和精度。
英文摘要：
In this paper, a computational method for predicting the aero-heating environment for key places of hypersonic aircrafts is presented. Based on the reference enthalpy method,the classical heat flux formulae are used to determine the surface aero-dynamic heating. Then, an algorithm for hypersonic aerodynamic heating environment is developed. Using this method, heating rates for some simple blunted cone shapes of aircrafts are calculated. The computational results show the high accuracy comparing to the existing experimental data.
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