超声速横向喷流侧向控制的数值模拟

李亚超; 阎超; 张翔; 孟军

doi:10.13700/j.bh.1001-5965.2014.0398

超声速横向喷流侧向控制的数值模拟

doi: 10.13700/j.bh.1001-5965.2014.0398

北京航空航天大学航空科学与工程学院, 北京 100191

详细信息

作者简介:
李亚超(1989—),男,河南许昌人,硕士研究生,yachaoli@foxmail.com

通讯作者:
阎超(1962—),男,江苏徐州人,教授,yanchao@buaa.edu.cn,主要研究方向为高超声速空气动力学.

中图分类号: V221⁺.3;TB553
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出版历程
- 收稿日期: 2014-07-03
- 网络出版日期: 2015-06-20

Numerical simulation of lateral control in supersonic cross jet flow

School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 为研究来流攻角和喷流位置对横向喷流侧向控制力的影响,通过数值方法模拟了超声速条件下的横向喷流干扰流场,计算得到的壁面沿程压力分布与实验结果吻合良好.采用喷流力放大因子和实际作用位置表征喷流侧向控制力的实际作用效果,引入法向干扰力沿程增加系数来分析弹体表面的压力特征区域对侧向控制力的影响.计算结果表明:在喷流干扰下,侧向控制力大小不等于喷流设计推力,并带有绕喷流中心位置的低头力矩;低压尾迹区是影响侧向力实际作用效果的决定因素;攻角的增大和喷流位置的后移,分别有助于削弱低压尾迹区的干扰强度和作用范围,从而增强侧向控制力的实际作用效果.
- 横向喷流 /
- 侧向控制力 /
- 攻角 /
- 喷流位置 /
- 低压尾迹区
Abstract: To investigate the effect of angle of attack and jet position on the lateral control force in the cross jet flow, the paper firstly simulated the supersonic cross jet flow by the numerical methods. The calculated longitudinal wall pressure distribution agreed well with the experimental results. Jet force amplification factor in longitudinal direction and center of interaction force were used to evaluate the actual performance of lateral control force in jet interaction. Moreover, normal interaction force accumulation coefficient was introduced to analyze how four characteristic areas on the body surface affect the lateral control force in jet interaction. The numerical results indicate that the lateral control force in jet interaction, which is equivalent to a normal force, together with a nose-down moment around center of jet, are not equal to the jet force in design. The wake zone of low pressure is a determinant factor affecting the actual performance of lateral control force. As the angle of attack increases, the strength of the interaction pressure in the wake zone decreases, which will enhance the lateral control force. With the jet location moving backward, the scope of the wake zone diminishes, which will improve the actual performance of lateral control force.
- cross jet /
- lateral control force /
- angle of attack /
- jet position /
- wake zone of low pressure

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参考文献(15)

[1]	李素循.激波与边界层主导的复杂流动[M].北京:科学出版社, 2007:167-170. Li S X.Complicated flow governed by shock and boundary layer[M].Beijing:Science Press, 2007:167-170(in Chinese).
[2]	Srivastava B.Computational analysis and validation for lateral jetcontrolled missiles[J].Journal of Spacecraft and Rockets, 1997, 34(5):584-592.
[3]	DeSpirito J.Factors affecting reaction jet interaction effects on projectiles, AIAA-2011-3031[R].Reston:AIAA, 2011.
[4]	Zhang J M, Cai J S, Cui Y D.Effect of nozzle shapes on lateral jets in supersonic cross flows, AIAA-2009-1477[R].Reston:AIAA, 2009.
[5]	Ibrahim I M, Murugappan S, Gutmark E J.Penetration, mixing andturbulent structures of circular and non-circular jets incross flow, AIAA-2005-0300[R].Reston:AIAA, 2005.
[6]	Li Z, Murugappan S, Gutmark E, et al.Numerical simulation and experiments of jets in cross flow, AIAA-2006-0307[R].Reston:AIAA, 2006.
[7]	Srivastava B.Lateral jet control of a supersonic missile:Compu-tational and experimental comparisons[J].Journal of Spacecraft and Rockets, 1998, 35(2):140-146.
[8]	阎超.计算流体力学方法与应用[M].北京:北京航空航天大学出版社, 2006:18-25. Yan C.Methods and application of computational fluid dynamics[M].Beijing:Beihang University Press, 2006:18-25(in Chinese).
[9]	闫宝琴, 李素循, 许能喜.横向喷流引起的三维复杂干扰流场结构研究[J].流体力学实验与测量, 2004, 18(3):59-63. Yan B Q, Li S X, Xu N X.Study of a 3D complex interference flow field structure induced by transverse jet[J].Experiments and Measurements in Fluid Mechanics, 2004, 18(3):59-63(in Chinese).
[10]	Liu T, Woodiga S. Experimental examination of skin friction topology in separated flows, AIAA-2010-0045[R].Reston:AIAA, 2010.
[11]	Graham M, Weinacht P, Brandeis J.Numerical investigation of supersonic jet interaction for finned bodies[J].Journal of Spacecraft and Rockets, 2002, 39(3):376-383.
[12]	耿云飞.高超声速飞行器减阻防热新方法数值模拟研究[D].北京:北京航空航天大学, 2011. Geng Y F.Numerical simulation of the new methods of drag reduction and thermal protection in the hypersonic vehicle design[D].Beijing:Beijing University of Aeronautics and Astronautics, 2011(in Chinese).
[13]	Graham M, Weinacht P.Numerical investigation of supersonic jetinteraction for axisymmetric bodies[J].Journal of Spacecraft and Rockets, 2000, 37(5):675-683.
[14]	Gruber M R, Nejad A S, Chen T H, et al.Transverse injection from circular and elliptic nozzles into a supersonic cross flow[J].Journal of Propulsion and Power, 2000, 16(3):449-457.
[15]	Julius B, Jacob G.Experimental investigation of super- and hypersonicjet interaction on missile configurations[J].Journal of Spacecraft and Rockets, 1998, 35(3):296-302.