超声速场中的反向喷流数值模拟

田婷; 阎超

超声速场中的反向喷流数值模拟

田婷,
阎超

北京航空航天大学航空科学与工程学院, 北京 100083

详细信息

中图分类号: V 211.3
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出版历程
- 收稿日期: 2006-12-27
- 网络出版日期: 2008-01-31

Numerical simulation on opposing jet in hypersonic flow

Tian Ting,
Yan Chao

School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

摘要: 采用了高分辨率的N-S(Navier-Stockes) 方程数值模拟方法,对钝头体头部反向喷流进行研究.计算并分析了头部反向喷流现象中喷流马赫数、来流马赫数、攻角等因素对流场细致结构的影响,并对反向喷流减少阻力和减少气动加热的原理进行了深入分析和探讨.研究分析表明这些因素通过决定弓形激波、马赫盘的强度和位置,来影响回流区的大小和位置,从而使有反向喷流时阻力系数所受到的影响比无喷流时更大.
- 反向喷流 /
- 高超声速 /
- 阻力 /
- 数值模拟
Abstract: The detailed influences of the free mach number, jet mach number, attack angle on the drag coefficient reduction were studied by high precise simulation of N-S(Navier-Stockes) equations. The Numerical results show good agreement with the experiments. It is indicated that the opposing jet is effective in reducing the aerodynamic heating and drag coefficient. Conclusions were got that the opposing jet enlarges the factors of affections by influencing the strength and the positions of the barrel shock, the mach disk and the recirculation region. It is believed that the drag coefficient turns out to be very sensitive to the flow field-s structure which is highly depended on the free mach number, jet mach number and attack angle due to the opposing jet.
- opposing jet /
- hypersonic /
- drag /
- numerical simulation

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参考文献(1)

[1] Hayashi K, Aso S, Tani Y. Numerical study of thermal protection system by opposing jet . AIAA 2005-188, 2005 [2] Hayashi K, Aso S. Effect of pressure ratio on aerodynamic heating reduction due to opposing jet . AIAA 2003-4041, 2003 [3] Wada Y, Liou M S. A flux splitting scheme with high-resolution and robustness for discontinuities . AIAA 94-0083, 1994 [4] Finley P J. The flow of a jet from a body opposing a supersonic free stream[J]. Journal of Fluid Mechanics, 1966, 26:265-272 [5] Fujita M.Axisymmetric oscillations of an opposing jet from a hemispherical nose . AIAA 1995-33(10), 1955 [6] Aso S, Hayashi K, Mizoguchi M. A study on aerodynamic heating reduction due to opposing jet in hypersonic flow . AIAA 2002-0646, 2002 [7] 刘君,张涵信,高树椿.超声速主流中逆向喷流流场的数值模拟[J].空气动力学报,1994,12(4):383-390 Liu Jun, Zhang Hanxin, Gao Shuchun. Numerical simulation for the flow of a jet from a body opposing a supersonic free stream[J].ACTA Aerodynamic Sinica, 1994, 12(4):383-390(in Chinese) [8] 耿湘人,桂业伟,王安龄.利用二维平面和轴对称逆向喷流减阻和降低热流的计算研究[J].空气动力学学报,2006,24(1): 85-89 Geng Xiangren, Gui Yewei, Wang Anling. Numerical investigation on drag and heat-transfer reduction using 2-D planar and axisymmetrical for ward facing jet[J]. ACTA Aerodynamic Sinica, 2006, 24(1):85-89(in Chinese) [9] 周伟江,马汉东.反向喷流与主流干扰数值模拟[J].空气动力学学报,1994,12(3):295-300 Zhou Weijiang, Ma Handong. Numerical simulation of the interaction between a supersonic stream and a countering nose jet[J]. ACTA Aerodynamic Sinica, 1994, 12(3):295-300(in Chinese) [10] 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 and mesh effect of computation fluid dynamic in aerothermal[J]. Journal of Beijing University of Aeronautics and Astronautics, 2003, 29(11):1022-1025(in Chinese) [11] 阎超,李君哲.热流CFD计算中格式和网格效应若干问题研究[J].空气动力学报,2006,24(1):125-130 Yan Chao, Li Junzhe. A new method to determine the first mesh-s height of computational fluid dynamic in aerothermal[J]. ACTA Aerodynamic Sinica, 2006, 24(1):125-130(in Chinese)

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