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This study experimentally investigates the aerodynamic performance enhancement of a NACA0012 aerofoil at a low Reynolds number of Rec = 2.6 × 104 through passive flow control. A micro cylinder rod (diameter d = 1.34% of chord length) was positioned upstream of the leading edge at varying distances (1 × d to 4 × d) to function as a vortex generator. Wind tunnel measurements, including hot-wire anemometry (HWA) for wake characterization and parietal oil stain visualization for flow structure assessment, were conducted to evaluate the control effectiveness. At low angles of attack (α < 10°), the rod suppressed the nonlinear lift variation characteristic of baseline low-Reynolds-number flows. For higher angles (α > 10°), optimal rod placement produced a significant increase in lift coefficient. The parietal oil stain visualization revealed that the rod injected freestream momentum into the boundary layer, delaying flow separation and reducing wake width, which correlated with measured drag reduction. This visualization technique provided clear evidence of separation point movement and boundary layer modification, demonstrating the rod’s effectiveness as a passive control device. .

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Experimental Investigation of the Effect of Small Off-Surface Vortex Generator on the Aerodynamic Performance of NACA0012 at Low Reynolds Number

  • 会议论文

  • 发表日期：

    2026年

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  • Abderrahim Larabi,
  • Michael Pereira,
  • Amrid Mammeri,
  • Tarik Azzam,
  • Hamid Oualli,
  • Florent Ravelet,
  • Farid Bakir

摘要

This study experimentally investigates the aerodynamic performance enhancement of a NACA0012 aerofoil at a low Reynolds number of Rec = 2.6 × 104 through passive flow control. A micro cylinder rod (diameter d = 1.34% of chord length) was positioned upstream of the leading edge at varying distances (1 × d to 4 × d) to function as a vortex generator. Wind tunnel measurements, including hot-wire anemometry (HWA) for wake characterization and parietal oil stain visualization for flow structure assessment, were conducted to evaluate the control effectiveness. At low angles of attack (α < 10°), the rod suppressed the nonlinear lift variation characteristic of baseline low-Reynolds-number flows. For higher angles (α > 10°), optimal rod placement produced a significant increase in lift coefficient. The parietal oil stain visualization revealed that the rod injected freestream momentum into the boundary layer, delaying flow separation and reducing wake width, which correlated with measured drag reduction. This visualization technique provided clear evidence of separation point movement and boundary layer modification, demonstrating the rod’s effectiveness as a passive control device. .