## 留言板

 引用本文: 康宏琳, 阎超, 李亭鹤, 等 . 高超声速再入钝头体表面热流计算[J]. 北京航空航天大学学报, 2006, 32(12): 1395-1398.
Kang Honglin, Yan Chao, Li Tinghe, et al. Numerical study of aeroheating predictions for hypersonic reentry bodies[J]. Journal of Beijing University of Aeronautics and Astronautics, 2006, 32(12): 1395-1398. (in Chinese)
 Citation: Kang Honglin, Yan Chao, Li Tinghe, et al. Numerical study of aeroheating predictions for hypersonic reentry bodies[J]. Journal of Beijing University of Aeronautics and Astronautics, 2006, 32(12): 1395-1398. (in Chinese)

## 高超声速再入钝头体表面热流计算

###### 作者简介:康宏琳(1979-),女,江西新余人,博士生,kanglin@ase.buaa.edu.cn.
• 中图分类号: V 211.3

## Numerical study of aeroheating predictions for hypersonic reentry bodies

• 摘要: 基于跟踪流线的轴对称比拟法,采用纯工程算法、Euler数值计算与边界层内工程算法相结合的方法,对高超声速再入钝头体的表面热流进行了计算,并将计算结果与风洞实验数据进行了对比,两者吻合较好,验证了两种工程算法在计算高超声速飞行器热环境方面的正确性.将两种工程算法与数值求解N-S方程进行对比,表明工程算法在迎风面的热流计算方面有较高的精度,节约了计算时间,很好地满足高超声速飞行器概念研究和设计的需要.

•  [1] Peter A G. Computational fluid dynamics technology for hypersonic applications . AIAA-2003-2829, 2003 [2] Dietiker J F, Hoffmann K A. Challenges in the heat transfer computations of high speed flows . AIAA-2004-0993, 2004 [3] 李君哲, 阎超. 气动热CFD计算的格式效应研究[J]. 北京航空航天大学学报, 2003, 29(11):1022-1025 Li Junzhe, Yan Chao. Research on scheme effect of computational fluid dynamics in aerothermodynamics[J]. Journal of Beijing University of Aeronautics and Astronautics, 2003, 29(11):1022-1025(in Chinese) [4] 王发民, 沈月阳, 姚文秀. 高超声速升力体气动力气动热数值计算[J]. 空气动力学学报, 2001, 19(4):439-445 Wang Famin,Shen Yueyang,Yao Wenxiu. Aerodynamic and aerothermal numerical simulation of hypersonic lifting body configuration[J].ACTA Aerodynamica Sinica, 2001,19(4):439-445(in Chinese) [5] Kinney D J. Aero-thermodynamics for conceptual design . AIAA-2004-0041, 2004 [6] Wurster K E, Zoby E V, Thompson R A. Flowfield and vehicle parameter influence on results of engineering aerothermal methods[J]. Journal of Spacecraft,1991,28(1):16-22 [7] Hamilton H H, Franceis A G. Approximate method for calculating heating rates on three-dimensional vehicles[J]. Journal of Spacecraft and Rockets,1994,31(3):345-354 [8] Dejarnette F R, Tai T C. A method for calculating laminar and turbulent convective heat transfer over bodies at an angle of attack .NASA-CR-101678, 1969 [9] Miller C G. Experimental and predicted heating distributions for biconics at incidence in air at mach 10 . NASA-TP-2334, 1984 [10] Cleary J W. Effects of angle of attack and bluntness on laminar heating rate distribution of a 15°cone at a mach number of 10.6 . NASA-TND-5450, 1969

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##### 出版历程
• 收稿日期:  2005-12-12
• 刊出日期:  2006-12-31

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