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Volume 41 Issue 5
May  2015
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Journal of Beijing University of Aeronautics and Astronautics  > 2015  >  41(5): 897-903.
ZHENG Yuning, QIU Zhiping, HUANG Ren, et al. Robust design optimization of a two-dimensional airfoil with deformable trailing edge[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(5): 897-903. doi: 10.13700/j.bh.1001-5965.2014.0387(in Chinese)
Citation: ZHENG Yuning, QIU Zhiping, HUANG Ren, et al. Robust design optimization of a two-dimensional airfoil with deformable trailing edge[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(5): 897-903. doi: 10.13700/j.bh.1001-5965.2014.0387(in Chinese)
shu

Robust design optimization of a two-dimensional airfoil with deformable trailing edge

doi: 10.13700/j.bh.1001-5965.2014.0387
  • 1.

    School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

  • 2. Beijing Electron-Mechanical Engineering Institute, Beijing 100074, China

  • Received Date: 30 Jun 2014
  • Rev Recd Date: 19 Sep 2014
  • Publish Date: 20 May 2015
    Abstract
  • In order to improve the aerodynamic stability of a two-dimensional airfoil with deformable trailing edge during the change of external conditions, a robust optimization method considering the uncertainty was proposed. Based on class-shape function transformation (CST) method, a parametric model was established to represent the geometry of a two-dimensional airfoil with a deformable trailing edge. The differences between robust optimization method and deterministic optimization method were discussed. Taking into account the uncertain airfoil geometry and inlet Mach number, the robust optimization method was applied to maximize the mean value of the lift-to-drag ratio and minimize its standard deviation. The actuation power requirement of the optimized airfoil with a deformable trailing edge was calculated. The results show that the robust optimization method can help to improve the aerodynamic performance of morphing airfoil and reduce the sensitivity of this performance to inlet Mach number simultaneously and to reduce the actuation power requirement of the robust optimal airfoil.

     

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