Volume 35 Issue 2
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SHI Hengtao, LIU Baojie, YU Xianjun. Polynomial-based continuous-curvature leading edge design method and its application[J]. Journal of Aerospace Power, 2020, 35(2): 397-409. doi: 10.13224/j.cnki.jasp.2020.02.019
Citation: SHI Hengtao, LIU Baojie, YU Xianjun. Polynomial-based continuous-curvature leading edge design method and its application[J]. Journal of Aerospace Power, 2020, 35(2): 397-409. doi: 10.13224/j.cnki.jasp.2020.02.019
shu

Polynomial-based continuous-curvature leading edge design method and its application

doi: 10.13224/j.cnki.jasp.2020.02.019
  • 1.

    School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China

  • 2.

    National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics,School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China

  • Received Date: 2019-07-27
  • Publish Date: 2020-02-28
    Abstract
  • To optimize the leading edge (LE) shape for improving airfoil aerodynamic performance, a polynomial based continuous-curvature LE design method was proposed. By specifying derivatives of camber-line and thickness distribution at the junction point, the continuous surface curvature was guaranteed. The length and the fullness of the LE portion could be specified according to design need. The method was used to optimize the LE portion of two subsonic airfoils with inlet Mach number of 075 and 060, respectively. Simulations indicated that the LE optimized airfoils had much lower suction spike strength, which decreased the gradient of adverse pressure caused by flow diffusion. Therefore, the LE separation bubble was suppressed and the premature transition of boundary-layer was avoided. Due to these two factors, the LE optimized airfoils had much lower loss level at off-design conditions and the useful operation range were increased by 31°and 38° compared with circular LE airfoil, respectively. The leading edge of a transonic compressor stage was also modified by this method, the increase of adiabatic efficiency for rotor and stage were 07 percent and 11 percent at near stall condition, respectively, with stall margin also extended.

     

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