拉瓦尔喷管外发生激波反射工况详细分析

于勇; 徐新文

拉瓦尔喷管外发生激波反射工况详细分析

于勇,
徐新文

北京理工大学宇航学院, 飞行器动力学与控制教育部重点实验室, 北京 100081

基金项目: 国家自然科学基金(10702009); 飞行器动力学与控制教育部重点实验室开放基金(GFTD0803)

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出版历程
- 收稿日期: 2011-08-30
- 刊出日期: 2012-09-28

Further detailed analysis about shock wave reflection outside Laval nozzle in different working states

YU Yong,
XU Xin-wen

Key Laboratory of Dynamics and Control of Flight Vehicle, Ministry of Education, School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China

摘要

摘要: 平面拉瓦尔喷管的环境压力与入口总压的比值从设计工况到第三极限工况(管口处为正激波)逐渐增大时,喷管外的激波现象不同.根据已知的激波反射理论,将设计工况到第三极限工况间的工作状况进一步细分为强斜激波工况、马赫反射工况、双解区和正规反射工况、并将由气流偏转角所表示的发生正规反射和马赫反射的条件用环境压力与总压的比值来表示,找出了强、弱斜激波的环境压力与总压比值的临界值,得到这些临界值随着喷管面积比的变化趋势.最后针对面积比为5的平面拉瓦尔喷管,由理论分析得到其管外发生正规反射、马赫反射、强斜激波反射时对应的压比分别为:0.0841,0.0959和0.2005,并用数值模拟来验证理论分析的正确性.
- 拉瓦尔喷管 /
- Von Neumann准则 /
- 正规反射 /
- 马赫反射 /
- 强斜激波
Abstract: When ratio of environmental pressure to total pressure increases from design state to third limit condition (normal shock at the outlet of nozzle), there are different shock wave phenomena outside the Laval nozzle. According to extant theory about shock wave reflection, the working range between design condition and the third limit condition was subdivided into several sections: strong oblique shock wave condition, Mach reflection condition, regular reflection and dual solution domain. Three critical ratios of environmental pressure to total pressure were proposed and determined to replace flow-deviation angle for estimating different Laval nozzle working statuses. Varying tendency of these critical ratios of Laval nozzle in various aspect ratios were also given with a figure. The pressure ratios corresponding regular reflection, Mach reflection and strong oblique wave in a planar Laval nozzle with aspect ratio 5 were 0.0841, 0.0959 and 0.2005 respectively, and then the accuracy of these values were verified with numerical simulation.
- Laval nozzle /
- Von Neumann criterion /
- regular reflection /
- Mach reflection /
- strong shock wave

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参考文献(15)

[1]	童秉纲,孔祥言,邓国华.气体动力学[M].北京:高等教育出版社,1990.
[2]	王保国,刘淑艳,黄光伟.气体动力学[M].北京:北京理工大学出版社,2005.
[3]	吴子牛,王兵,周睿等.空气动力学[M].北京:清华大学出版社,2008.
[4]	王新月.气体动力学基础[M].西安:西北工业大学出版社,2006.
[5]	周文祥,黄金泉.拉瓦尔喷管计算模型的改进及其整机仿真验证[J].航空动力学报,2009,24(11):2601-2605. ZHOU Wenxiang,HUANG Jinquan.Improvement of Laval nozzle calculation model and simulative verification in aero-engine performance calculation[J].Journal of Aerospace power,2009,24(11):2601-2605.(in Chinese)
[6]	钱翼稷.空气动力学[M].北京:北京航空航天大学出版社,2004.
[7]	Ben-Dor G.Shock wave reflection phenomena[M].2nd ed. New York:Springer,2007.
[8]	谭廉华.平面与轴对称定常激波马赫反射中的激波形状研究. 北京:清华大学,2007. TAN Lianhua.On the shape of shock waves in steady planar and axisymmetical Mach reflections. Beijing:Tsinghua University,2007.(in Chinese)
[9]	Gao B,Wu Z N.A study of the flow structure for Mach reflection in steady supersonic flow[J].Journal of Fluid Mechanics,2010,656:29-50.
[10]	Ben-Dor G,Ivanov M,Vasilev E I,et al.Hysteresis processes in the regular reflection:Mach reflection transition in steady flows[J].Progress in Aerospace Sciences,2002,38(4/5):347-387.
[11]	Sudani N,Sato M,Karasawa T,et al.Irregular effects on the transition from regular to Mach reflection of shock waves in wind tunnel flows[J].Journal of Fluid Mechanics,2002,459:167-185.
[12]	Shimshi E,Ben-Dor G.Viscous simulation of shock-reflection hysteresis in overexpanded planar nozzles[J].Journal of Fluid Mechanics 2009,635:189-206.
[13]	TAN Lianhua,REN Yuxin,WU Ziniu.Analytical and numerical study of the near flow field and shape of the Mach stem in steady flows[J].Journal of Fluid Mechanics,2006,546(01):341-362.
[14]	Hornung H G,Schwendeman D W.Oblique shock reflection from an axis of symmetry:shock dynamics and relation to the Guderley singularity[J].Journal of Fluid Mechanics,2001,438:231-245.
[15]	Li S G,Gao B,Wu Z N.Time history of regular to Mach reflection transition in steady supersonic flow[J].Journal of Fluid Mechanics,2011,682:160-184.