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小攻角对后掠机翼边界层稳定性及转捩的影响

靖振荣 孙朋朋 黄章峰

靖振荣, 孙朋朋, 黄章峰等 . 小攻角对后掠机翼边界层稳定性及转捩的影响[J]. 北京航空航天大学学报, 2015, 41(11): 2177-2183. doi: 10.13700/j.bh.1001-5965.2014.0769
引用本文: 靖振荣, 孙朋朋, 黄章峰等 . 小攻角对后掠机翼边界层稳定性及转捩的影响[J]. 北京航空航天大学学报, 2015, 41(11): 2177-2183. doi: 10.13700/j.bh.1001-5965.2014.0769
JING Zhenrong, SUN Pengpeng, HUANG Zhangfenget al. Effect of attack angle on stability and transition in a swept-wing boundary layer[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(11): 2177-2183. doi: 10.13700/j.bh.1001-5965.2014.0769(in Chinese)
Citation: JING Zhenrong, SUN Pengpeng, HUANG Zhangfenget al. Effect of attack angle on stability and transition in a swept-wing boundary layer[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(11): 2177-2183. doi: 10.13700/j.bh.1001-5965.2014.0769(in Chinese)

小攻角对后掠机翼边界层稳定性及转捩的影响

doi: 10.13700/j.bh.1001-5965.2014.0769
基金项目: 国家自然科学基金(11332007);空气动力学国家重点实验室开放课题(SKLA201401)
详细信息
    作者简介:

    靖振荣(1992-),男,河北邯郸人,硕士研究生,zrjing@tju.edu.cn

    通讯作者:

    黄章峰(1977-),男,湖南宜章人,副教授,hzf@tju.edu.cn,主要研究方向为流动稳定性、转捩及湍流、直接数值模拟.

  • 中图分类号: V211.1+9;O357.4+1

Effect of attack angle on stability and transition in a swept-wing boundary layer

  • 摘要: 攻角是影响后掠机翼边界层横流稳定性的关键参数之一.以NACA0012翼型为研究对象,通过求解三维可压缩Navier-Stokes方程计算了展向无限长后掠机翼的基本流场;通过求解Orr-Sommerfeld方程得到了扰动波的中性曲线及增长率演化曲线,基于线性稳定性理论(LST)研究了攻角对后掠机翼边界层流动稳定性的影响;最后采用转捩预测eN方法进行了转捩预测.研究发现,扰动波的增长在背风面受到抑制,在迎风面受到增强;转捩首先发生在迎风面,当扰动速度为来流速度的0.05%时,转捩发生的N值在6左右,转捩发生的位置在0.1~0.2个弦长之间.

     

  • [1] Joslin R D.Overview of laminar flow control[M].Virginia:National Aeronautics and Space Administration, Langley Research Center, 1998.
    [2] 周恒,赵耕夫.流动稳定性[M].北京:国防工业出版社, 2004:157-158. Zhou H, Zhao G F.Hydrodynamic stability[M].Beijing:National Defense Industry Press, 2004:157-158(in Chinese).
    [3] 吴永健.横流不稳定性实验研究[D].南京:南京航空航天大学, 2002. Wu Y J.Experimental study on crossflow instabilities in the boundary-layer of swept wing[D].Nanjing:Nanjing University of Aeronautics and Astronautics, 2002(in Chinese).
    [4] Boltz F W, Kenyon G C, Allen C Q.Effects of sweep angle on the boundary-layer stability characteristics of an untapered wing at low speeds, Technical Note:D-338[R].Moffett Field:National Aeronautics and Space Administration, 1960.
    [5] Haynes T S.Nonlinear stability and saturation of crossflow vortices in swept-wing boundary layers[D].Tempe:Arizona State University, 1996.
    [6] Dagenhart J R, Saric W S.Crossflow stability and transition experiments in swept-wing flow[M].Virginia:National Aeronautics and Space Administration, Langley Research Center, 1999:1, 7.
    [7] Reibert M S, Saric W S.Review of swept-wing transition, AIAA-1997-1816[R].Reston:AIAA, 1997.
    [8] Bushnell D M, Malik M R, Harvey W D.Transition prediction in external flows via linear stability theory[C]//Symposium Transsonicum Ⅲ.Berlin Heidelberg:Springer-Verlag, 1988:225.
    [9] Arnal D, Gasparian G, Salinas H.Recent advances in theoretical methods for laminar-turbulent transition prediction[J].AIAA, 1998:98-0223.
    [10] 孙朋朋,黄章峰.后掠角对后掠机翼边界层稳定性及转捩的影响[J].北京航空航天大学学报, 2015, 41(7):1313-1321. Sun P P, Huang Z F.Effect of the sweep angle on the stability and transition in a swept-wing boundary layer[J].Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(7):1313-1321(in Chinese).
    [11] 李锋,汪翼云,崔尔杰.翼型大攻角绕流的数值模拟[J].航空学报, 1992, 13(1):17-22. Li F, Wang Y Y, Cui E J.The numerical simulation of compressible flow around an airfoil at high angle of attack[J].Acta Aeronautica et Astronautica Sinica, 1992, 13(1):17-22(in Chinese).
    [12] 吴鋆,王晋军,李天.NACA0012翼型低雷诺数绕流的实验研究[J].实验流体力学, 2013, 27(6):32-38. Wu J, Wang J J, Li T.Experimental investigation on low Reynolds number behavior of NACA0012 airfoil[J].Journal of Experiments in Fluid Mechanics, 2013, 27(6):32-38(in Chinese).
    [13] 吴鋆,李天,王晋军.低Reynolds数NACA0012翼型绕流的流动特性分析[J].实验力学, 2014, 29(3):265-272. Wu J, Li T, Wang J J.Characteristic analysis of flow around NACA0012 airfoil in a low-Reynold-number media[J].Journal of Experimental Mechanics, 2014, 29(3):265-272(in Chinese).
    [14] 袁湘江,李国良,刘智勇,等.小攻角高超声速钝锥边界层失稳特性[J].航空动力学报, 2011, 26(12):2805-2811. Yuan X J, Li G L, Liu Z Y, et al.Study of the instability characteristic in the boundary layer of a hypersonic blunt cone at low angle of attack[J].Journal of Aerospace Power, 2011, 26(12):2805-2811(in Chinese).
    [15] 王斌,白存儒,杨广郡,等.后掠机翼低速流动转捩位置的升华法测量[J].实验力学, 2009, 24(3):197-201. Wang B, Bai C R, Yang G J, et al.Measurement of transition location change of swept wing in a low speed flow based on sublimation method[J].Journal of Experimental Mechanics, 2009, 24(3):197-201(in Chinese).
    [16] 孙朋朋.马赫数、攻角及后掠角对后掠机翼边界层稳定性及转捩的影响[D].天津:天津大学, 2015. Sun P P.Effect of Mach number, attack angle and sweep angle on the stability and transition in a swept-wing boundary layer[D].Tianjin:Tianjin University, 2015(in Chinese).
    [17] 黄章峰,逯学志,于高通.机翼边界层的横流稳定性分析和转捩预测[J].空气动力学学报, 2014, 32(1):14-20. Huang Z F, Lu X Z, Yu G T.Cross-flow instability analysis and transition prediction of airfoil boundary layer[J].ACTA Aerodynamic Sinica, 2014, 32(1):14-20(in Chinese).
    [18] 韩步璋,黄奕裔,张其威,等.NACA0012翼型跨音速测压实验研究[J].南京航空航天大学学报, 1987, 19(2):92-102. Han B Z, Hang Y Y, Zhang Q W, et al.An experiment of pressure measurement for NACA0012 airfoil in a transonic wind tunnel[J].Journal of Nanjing Aeronautical Institute, 1987, 19(2):92-102(in Chinese).
    [19] Huang Z F, Cao W, Zhou H.The mechanism of breakdown in laminar-turbulent transition of a supersonic boundary layer on a flat plate-temporal mode[J].Science in China Series G:Mechanics and Astronomy, 2005, 48(5):614-625.
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出版历程
  • 收稿日期:  2014-12-08
  • 修回日期:  2015-01-23
  • 刊出日期:  2015-11-20

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