| 高超音速飞行器气动加热计算 |
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| 引用本文： | 雷延花,徐敏,陈士橹.高超音速飞行器气动加热计算[J].上海航天,2001,18(5):10-13. |
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| 作者姓名： | 雷延花 徐敏 陈士橹 |
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| 作者单位： | 西北工业大学, |
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| 摘 要： | 对高超音速飞行器气动加热计算方法进行研究，采用基于热流量平衡方程的工程估算方法和二维薄层近似N－S方程数值模拟，计算高超音速飞行器对称面中心线上的温度分布。以天地往返运输系统的气动加热为例进行了计算，并对计算结果进行了分析和比较，计算结果表明：该工程估算方法和数值计算方法是可行的。
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| 关 键 词： | 高超音速飞行器 气动加热 计算方法 数值模拟 工程估算 温度分布 再入阶段 |
| 文章编号： | 1006-1630(2001)05-0010-04 |
| 修稿时间： | 2000年11月28 |
The Aerothermal Calculation of Hypersonic Vehicle |
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| LEI Yan-hua,XU Min,CHEN Shi-lu.The Aerothermal Calculation of Hypersonic Vehicle[J].Aerospace Shanghai,2001,18(5):10-13. |
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| Authors: | LEI Yan-hua XU Min CHEN Shi-lu |
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| Abstract: | This paper studies aerothermal calculative method of hypersonic vehicle. Temperature of hypersonic vehicle spin craft's body centerline has been calculated adopting the engineering prediction based on the flux balance equation and numerical simulation of two dimension thin layer N S Equation. As an example, the aerothermal calculation of fully reusable launch vehicle has been done. The results indicates that the engineering prediction and the numerical simulation proposed in this paper are workable. At last the calculated results have been analyzed and compared. |
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| Keywords: | Hypersonic vehicle Aerothermal heating Calculation Numerical simulation Engineering prediction |
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