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Volume 41 Issue 11
Nov.  2015
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Journal of Beijing University of Aeronautics and Astronautics  > 2015  >  41(11): 2177-2183.
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)
shu

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

doi: 10.13700/j.bh.1001-5965.2014.0769
  • 1.

    Department of Mechanics, Tianjin University, Tianjin 300072

  • 2. State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang 621000, China

  • Received Date: 08 Dec 2014
  • Rev Recd Date: 23 Jan 2015
  • Publish Date: 20 Nov 2015
    Abstract
  • Attack angle is one of the key parameters to the cross-flow instability of swept-wing boundary layers. For swept NACA0012 airfoil with infinite spanwise length, the basic flow field was calculated by solving the three-dimensional compressible Navier-Stokes equations numerically, the neutral curve and the evolution curve of growth rate were obtained by solving the Orr-Sommerfeld equation, the effect of attack angle on the cross-flow stability was analyzed by linear stability theory (LST), and the transition position was predicted by eN method. It is found that, the growth of unstable waves in the leeward is inhibited but enhanced in the windward. Transition firstly occurs in the windward, and the transition position predicted by eN method is about 0.1 to 0.2 of the chord length with the N factor of about 6 when the disturbance velocity is 0.05% of the free-stream velocity.

     

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