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后掠角对后掠机翼边界层稳定性及转捩的影响

孙朋朋 黄章峰

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. doi: 10.13700/j.bh.1001-5965.2014.0540
引用本文: 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. doi: 10.13700/j.bh.1001-5965.2014.0540
SUN Pengpeng, HUANG Zhangfeng. Effect of sweep angle on stability and transition in a swept-wing boundary layer[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(7): 1313-1321. doi: 10.13700/j.bh.1001-5965.2014.0540(in Chinese)
Citation: SUN Pengpeng, HUANG Zhangfeng. Effect of sweep angle on stability and transition in a swept-wing boundary layer[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(7): 1313-1321. doi: 10.13700/j.bh.1001-5965.2014.0540(in Chinese)

后掠角对后掠机翼边界层稳定性及转捩的影响

doi: 10.13700/j.bh.1001-5965.2014.0540
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(SKLA201301,SKLA201401)
详细信息
    作者简介:

    孙朋朋(1989—),男,山东德州人,硕士研究生,sunpp@tju.edu.cn

    通讯作者:

    黄章峰(1977—),副教授,湖南宜章人,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 sweep angle on stability and transition in a swept-wing boundary layer

  • 摘要: 后掠机翼边界层流动稳定性及转捩对翼型的设计及优化有着重要的参考价值,而机翼后掠角是引起后掠机翼边界层横流失稳的关键参数之一.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Tollmien-Schishting波演化的中性曲线及幅值曲线,研究了后掠角对后掠机翼边界层流动稳定性的影响;最后采用eN方法进行了转捩预测.研究发现,随后掠角的增大,横流强度和扰动幅值放大指数n均先增加后减小,且后掠角在40°~50°之间横流强度达到最大值.当后掠角在50°左右时,用转捩预测eN方法计算的幅值增长指数N值最大,导致转捩发生所需的初始扰动幅值最小,转捩最易发生.

     

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出版历程
  • 收稿日期:  2014-09-03
  • 修回日期:  2014-10-31
  • 刊出日期:  2015-07-20

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