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Volume 43 Issue 8
Aug.  2017
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Journal of Beijing University of Aeronautics and Astronautics  > 2017  >  43(8): 1616-1624.
XING Yu, LUO Dongming, YU Xiongqinget al. Optimization strategy of supercritical laminar flow airfoil design[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(8): 1616-1624. doi: 10.13700/j.bh.1001-5965.2016.0656(in Chinese)
Citation: XING Yu, LUO Dongming, YU Xiongqinget al. Optimization strategy of supercritical laminar flow airfoil design[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(8): 1616-1624. doi: 10.13700/j.bh.1001-5965.2016.0656(in Chinese)
shu

Optimization strategy of supercritical laminar flow airfoil design

doi: 10.13700/j.bh.1001-5965.2016.0656

  • Key Laboratory of Fundamental Science for National Defense Advanced Design Technology of Flight Vehicle, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Funds:

National Natural Science Foundation of China 11432007

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  • Corresponding author: YU Xiongqing, E-mail:yxq@nuaa.edu.cn
  • Received Date: 09 Aug 2016
  • Accepted Date: 14 Oct 2016
  • Publish Date: 20 Aug 2017
    Abstract

  • A two-step optimization strategy for the supercritical laminar flow airfoil design is proposed in the paper. The γ-Reθt transition model coupled with the shear stress transportation (SST) turbulence model is used for prediction of airfoil boundary layer transition. The Class/Shape Transformation (CST) method is used to parameterize airfoil geometry. The parameters in the airfoil geometry model are used as the design variables. The first step of optimization is to increase the ratio of the laminar flow region. A genetic algorithm based on the Kriging surrogate model is employed to obtain the laminar flow airfoil with all constraints satisfied. The second step of optimization is to improve the optimization result of the first step, and to further increase the lift-to-drag ratio of the airfoil. A gradient based optimization is used to search optimal solution. The aerodynamic analysis during the second step optimization is implemented through the CFD code rather than the surrogate model. The example demonstrates that the supercritical airfoil NASA SC(2) 0412 can be optimized into a supercritical laminar flow airfoil by the two-step optimization method, the laminar region ratios on the airfoil upper and lower surface increase by 55.5% and 47.0% respectively, and the lift-to-drag ratio increases by 38.1%.

     

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