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When flow over the upper surface of an airfoil begins to separate, it creates turbulence in which the air flow begins to produce vortices. It results in a decrease in lift and increase in drag. The flow separation can be delayed by imparting momentum to the fluid by providing a vortex generator (VG). Numerical investigations were done on NACA 0015 airfoil without and with VG in the form of a rotating cylinder in the present study. As a VG, ϕ15 mm cylinder with a length of 100 mm was provided at a maximum thickness section of the airfoil. The steady state simulations were carried out in ANSYS Fluent software in the wide range of Reynolds numbers (Re), i.e., 0.29–2.58 lacs at seven different angle of attacks (α), viz. 0°, 3°, 6°, 9°, 12°, 15° and 18°. Numerical analysis was carried out to find an optimum rotational speed of VG. In order to validate the numerical results, NACA 0015 wing was 3D printed and experiments were conducted in a low-speed wind tunnel developed indigenously. The flow separation point was delayed by 15–81% and the lift coefficient was increased up to 54% by the provision of VG.

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Performance Enhancement of NACA 0015 Wing Using Rotating Cylinder Vortex Generator

  • 会议论文

  • 发表日期：

    2026年

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  • S. N. Jadhav,
  • Akshay Gupta,
  • Akshaat Singh,
  • Harshvardhan Saxena,
  • S. V. Jain,
  • A. M. Achari,
  • T. N. Raval,
  • Ath Singhal

摘要

When flow over the upper surface of an airfoil begins to separate, it creates turbulence in which the air flow begins to produce vortices. It results in a decrease in lift and increase in drag. The flow separation can be delayed by imparting momentum to the fluid by providing a vortex generator (VG). Numerical investigations were done on NACA 0015 airfoil without and with VG in the form of a rotating cylinder in the present study. As a VG, ϕ15 mm cylinder with a length of 100 mm was provided at a maximum thickness section of the airfoil. The steady state simulations were carried out in ANSYS Fluent software in the wide range of Reynolds numbers (Re), i.e., 0.29–2.58 lacs at seven different angle of attacks (α), viz. 0°, 3°, 6°, 9°, 12°, 15° and 18°. Numerical analysis was carried out to find an optimum rotational speed of VG. In order to validate the numerical results, NACA 0015 wing was 3D printed and experiments were conducted in a low-speed wind tunnel developed indigenously. The flow separation point was delayed by 15–81% and the lift coefficient was increased up to 54% by the provision of VG.