Analysis of Owl-like Airfoil Aerodynamics at Low Reynolds Number Flow

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  • KONDO Katsutoshi
    1) Department of Mechanical Engineering, Tokyo University of Science
  • AONO Hikaru
    Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
  • NONOMURA Taku
    Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
  • ANYOJI Masayuki
    Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
  • OYAMA Akira
    Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
  • LIU Tianshu
    Department of Mechanical and Aeronautical Engineering, Western Michigan University
  • FUJII Kozo
    Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
  • YAMAMOTO Makoto
    1) Department of Mechanical Engineering, Tokyo University of Science

Abstract

Aerodynamic characteristics and flow fields around an owl-like airfoil at a chord Reynolds number of 23,000 are investigated using two-dimensional laminar flow computations. Computed results demonstrate that the deeply concaved lower surface of the owl-like airfoil contributes to lift augmenting, and both a round leading edge and a flat upper surface lead to lift enhancement and drag reduction due to the suction peak and the presence of the thin laminar separation bubble near the leading edge. Subsequently, the owl-like airfoil has higher lift-to-drag ratio than the high lift-to-drag Ishii airfoil at low Reynolds number. However, when the minimum drag is presented, the Ishii airfoil gains lift coefficient of zero while lift coefficient of the owl-like airfoil does not becomes zero. Furthermore, a feature of unsteady flow structures around the owl-like airfoil at the maximum lift-to-drag ratio condition is highlighted.

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