平流层飞艇尾部形状对气动阻力的影响

张海军; 郭雪岩; 杨帆; 戴韧

doi:10.13224/j.cnki.jasp.2015.03.005

平流层飞艇尾部形状对气动阻力的影响

doi: 10.13224/j.cnki.jasp.2015.03.005

上海理工大学能源与动力工程学院, 上海 200093

基金项目:

国家自然科学基金(51176127,51276116,10902070)

详细信息

作者简介:
张海军(1981-),男,江苏盐城人,博士生,主要研究方向为计算流体力学及气动优化方法.

通讯作者:
郭雪岩(1964-),男,辽宁兴城人,副教授,博士,主要研究方向为计算流体力学及气动优化方法.xyguo@usst.edu.cn

中图分类号: V211.3
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- 文章访问数: 1760
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- 被引次数: 0
出版历程
- 收稿日期: 2013-10-28
- 刊出日期: 2015-03-28

Influences of geometry of hull tail on aerodynamic drag of stratospheric airships

School of Energy and Power Engineering, University of Shanghai for Science and Technology, Shanghai 200093, China

摘要

摘要: 为了研究平流层飞艇尾部动量边界层厚度与尾涡结构,应用LES(大涡模拟)方法计算了零攻角工况下飞艇绕流场,并对LOTTE和M-LOTTE两种飞艇进行了对比分析.采用Q分布和涡量描述回转体尾涡结构,根据Q分布可以确定M-LOTTE飞艇较LOTTE飞艇尾部分离区显著减小;并分析了回转体的轴对称曲面动量边界层厚度对飞艇气动阻力的影响,随着飞艇尾部厚度逐渐减小,动量边界层厚度逐渐增大,M-LOTTE飞艇尾部动量边界层厚度明显小于LOTTE飞艇.飞艇尾部动量边界层厚度分布说明了M-LOTTE飞艇的总阻力系数较LOTTE飞艇降低17.2%的原因,同时也表明飞艇尾部形状对飞艇气动阻力影响较大.
- 平流层飞艇 /
- 大涡模拟 /
- LOTTE飞艇 /
- 动量边界层厚度 /
- 尾涡结构
Abstract: LES (large-eddy simulation) method was used to simulate the external flow field around hulls of the LOTTE and M-LOTTE airships at zero incidence angle in order to analyze the momentum boundary thickness and trailing vortex structure of stractospheric airship. Q distribution together with vorticity was used to visualize the trailing vortex structures of revolutional body. The Q distribution shows that compared with the LOTTE airship, the separation region in the tail of M-LOTTE airship is much smaller. Influence of axial symmetry momentum boundary layer thickness of revolutional bodies on aerodynamic drag of airship was analyzed. It has been found that the momentum boundary layer thickness increases obviously toward to the tail end for both of the two airship hulls and apparently thinner momentum boundary layer thickness exists for the M-LOTTE airship. The distribution of momentum boundary layer thickness explains the fact that the total drag coefficient of the M-LOTTE airship hull was 17.2% smaller than that of the LOTTE airship. It can be concluded that hull tail geometry of the airship can significantly determine the total aerodynamic drag.
- stratospheric airship /
- large-eddy simulation /
- LOTTE airship /
- momentum boundary thickness /
- trailing vortex structure

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参考文献(22)

[1]	Khoury G A,Gillet J D.Airship technology[M].Cambridge:Cambridge University Press,1999.
[2]	Li Y,Nahon M,Sharf I.Airship dynamics modeling:a literature review[J].Progress in Aerospace Sciences,2011,47(3):217-239.
[3]	Lutz T,Funk P,Jakobi A,et al.Summary of aerodynamic studies on the LOTTE airship[C]//Proceeding of the 4th International Airship Convention and Exhibition.Cambridge,UK:the Airship Assciation,2002:1-12.
[4]	Kreplin H P,Vollmers H,Meier H U.Measurements of the wall shear stress on an inclined prolate spheroid[J].Flugwiss Weltraumforsch,1982,6(4):248-252.
[5]	Chesnakas C J,Simpson R L.Detailed investigation of the three-dimensional separation about a 6∶1 prolate spheroid[J].AIAA Journal,1997,35(6):990-999.
[6]	Su W H,Tao B,Xu L.Three-dimensional separated flow over a prolate spheroid[J].AIAA Journal,1993,31(11):2175-2176.
[7]	Ahn S.An experimental study of flow over a 6 to 1 prolate spheroid at incidence[D].Blacksburg,VA:Virginia Polytechnic Institute and State University,1992.
[8]	Emre A,Lyle N L.Separated turbulent flow simulations using a Reynolds stress model and unstructured meshes[R].AIAA-2005-1094,2005.
[9]	张丹,郭雪岩.平流层双轴椭球体飞艇绕流场的数值分析[J].力学季刊,2008,29(4):556-564. ZHANG Dan,GUO Xueyan.Numerical analyses on ambient flow of a double-axis ellipsoidal stratospheric airship[J].Chinese Quarterly of Mechanics,2008,29(4):556-564.(in Chinese)
[10]	林瑞坤,郭雪岩.带螺旋桨平流层飞艇气动性能的数值模拟[J].力学季刊,2010,31(3):355-362. LIN Ruikun,GUO Xueyan.Numerical analysis of aerodynamic performance for stratospheric airship with a propeller[J].Chinese Quarterly of Mechanics,2010,31(3):355-362.(in Chinese)
[11]	Tezuka A,Suzuki K.Three-dimensional global linear stability analysis of flow around a spheroid[J].AIAA Journal,2006,44(8):1697-1708.
[12]	Constantinescu G S,Pasinato H,Wang Y Q,et al.Numerical investigation of flow past a prolate spheroid[J].Journal of Fluids Engineering,2002,124(4):904-910.
[13]	Xiao Z,Zhang Y,Huang J,et al.Prediction of separation flows around a 6∶1 prolate spheroid using RANS/LES hybrid approaches[J].Acta Mechanica Sinica,2007,23(4):369-382.
[14]	张海军,郭雪岩,戴韧.转捩对优化平流层飞艇外形的影响[J].航空动力学报,2013,28(7):1582-1590. ZHANG Haijun,GUO Xueyan,DAI Ren.Influences of transition on optimization of stratospheric airships hull[J].Journal of Aerospace Power,2013,28(7):1582-1590.(in Chinese)
[15]	Funk P,Lutz T,Wagner S.Experimental investigations on hull-fin interferences of the LOTTE airship[J].Aerospace Sciences and Technology,2003,7(8):603-610.
[16]	张兆顺,崔桂香,许春晓.湍流大涡数值模拟的理论和应用[M].北京:清华大学出版社,2008.
[17]	张楠,沈泓萃,姚惠之,等.水下航行体壁面脉动压力的大涡模拟研究[J].水动力学研究与进展,2010,25(1):106-112. ZHANG Nan,SHEN Hongcui,YAO Huizhi,et al.Large eddy simulation of wall pressure fluctuations of underwater vehicle[J].Chinese Journal of Hydrodynamics,2010,25(1):106-112.(in Chinese)
[18]	Jiang X,Lai C H.Numerical techniques for direct and large-eddy simulations[M].London,UK:CRC Press,Taylor & Francis Group,2009.
[19]	林瑞坤.带螺旋桨飞艇裸艇体气动性能的数值分析[D].上海:上海理工大学,2011.
[20]	Jeong J,Hussain F.On the identification of a vortex[J].Journal of Fluid Mechanics,1995,285:69-94.
[21]	Wang L.On properties of fluid turbulence along streamlines[J].Journal of Fluid Mechanics,2010,648:183-203.
[22]	Patel V C,Nakayama A,Damian R.Measurements in the thick axisymmetric turbulent boundary layer near the tail of a body of revolution[J].Journal of Fluid Mechanics,1974,63(2):345-367.