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<p>This paper utilizes the large eddy simulation capabilities to investigate the aerodynamic characteristics of NACA0012 airfoils modified with slits at low Reynolds number, which are consistent with previous research on flow control modifications. The effects of slit modifications near the leading and trailing edges are examined at varying angles of attack. The study models variations in the placement of slits to assess how these modifications influence the flow around the airfoil and improve aerodynamic performance. The configuration includes slits that allow flow to eject and suck at strategic points, enhancing boundary layer control, and adjusting the placement of slits to maximize the aerodynamic benefits across different flight regimes. It is observed that lift and drag forces vary depending on the slit configuration. The size of the laminar separation bubbles also varies depending on the placement and design of the slits, such as their proximity to critical aerodynamic regions and the degree of flow intervention they introduce. The majority of results indicate an improvement in the lift-to-drag ratio, demonstrating the potential of slit modifications to enhance airfoil efficiency.</p>

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Large-Eddy Simulation of Low Reynolds Number Flow Around Airfoils with Suction and Ejection Slits

  • 期刊论文

  • 发表日期：

    2025年7月8日

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  • Jinyu Li,
  • Koji Nagata,
  • Tomoaki Watanabe

摘要

This paper utilizes the large eddy simulation capabilities to investigate the aerodynamic characteristics of NACA0012 airfoils modified with slits at low Reynolds number, which are consistent with previous research on flow control modifications. The effects of slit modifications near the leading and trailing edges are examined at varying angles of attack. The study models variations in the placement of slits to assess how these modifications influence the flow around the airfoil and improve aerodynamic performance. The configuration includes slits that allow flow to eject and suck at strategic points, enhancing boundary layer control, and adjusting the placement of slits to maximize the aerodynamic benefits across different flight regimes. It is observed that lift and drag forces vary depending on the slit configuration. The size of the laminar separation bubbles also varies depending on the placement and design of the slits, such as their proximity to critical aerodynamic regions and the degree of flow intervention they introduce. The majority of results indicate an improvement in the lift-to-drag ratio, demonstrating the potential of slit modifications to enhance airfoil efficiency.