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This research investigates the impact of the Gurney flap on the aerodynamic performance of the NACA 0018 airfoil at a Reynolds number of Re = 1 × 105. A total of forty data sets are generated using the Halton sampling method, and computational fluid dynamics (CFD) simulations are performed on each set. The CFD outputs are then utilized to train a surrogate model based on the Kriging method. The optimization process employs the differential evolution algorithm to determine the optimal Gurney flap height, width and angle of attack values. The findings demonstrate that the optimized Gurney flap configuration leads to a significant enhancement in the lift coefficient, with an average increase of approximately 26.9%. These results underscore the effectiveness of the Gurney flap as a means to improve the aerodynamic performance of the NACA 0018 airfoil at the specified Reynolds number. Further investigations and experimental validations are recommended to validate the obtained results and explore potential applications in practical aerodynamic designs.

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Optimization of Gurney Flap Over NACA 0018 by Using Surrogate Modeling

  • 章节

  • 发表日期：

    2025年

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  • Emre Güler,
  • Mehmet Erdem,
  • Şıhmehmet Yıldız,
  • Melike Nikbay

摘要

This research investigates the impact of the Gurney flap on the aerodynamic performance of the NACA 0018 airfoil at a Reynolds number of Re = 1 × 105. A total of forty data sets are generated using the Halton sampling method, and computational fluid dynamics (CFD) simulations are performed on each set. The CFD outputs are then utilized to train a surrogate model based on the Kriging method. The optimization process employs the differential evolution algorithm to determine the optimal Gurney flap height, width and angle of attack values. The findings demonstrate that the optimized Gurney flap configuration leads to a significant enhancement in the lift coefficient, with an average increase of approximately 26.9%. These results underscore the effectiveness of the Gurney flap as a means to improve the aerodynamic performance of the NACA 0018 airfoil at the specified Reynolds number. Further investigations and experimental validations are recommended to validate the obtained results and explore potential applications in practical aerodynamic designs.