The aerodynamic performance of a NACA 63₃‐418 airfoil has been analyzed with disturbances in approximately 1000 different configurations focused on the frontal 10% of the airfoil. The configuration parameters are based on field test samples and rain erosion test specimens. The most important trends are presented by 500 configurations each simulated for 6°, 8°, and 10° angle of attack. The simulations are performed with the DTU Wind Energy in‐house 2D CFD Reynolds‐averaged Navier–Stokes solver, EllipSys2D, combined with the e^N transition model for the laminar‐turbulent boundary layer transition. The configurations are modeled by a direct geometrical modification of the airfoil shape. The results show that the most important parameters are the position and the depth/height of the disturbance, with up to 35% lift reduction and 90% lift/drag reduction within the specified angle of attacks and disturbance parameter ranges.

中文翻译：

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二维定量参数研究，简化了NACA 633-418机翼的空气动力学特性的表面缺陷

已对NACA 63 ₃ 418翼型的空气动力学性能进行了分析，并以翼型的前10％为重点，对大约1000种不同配置进行了扰动。配置参数基于现场测试样品和雨水侵蚀测试样品。最重要的趋势是通过500种配置呈现的，每种配置都针对6°，8°和10°迎角进行了仿真。仿真是使用DTU风能内部2D CFD雷诺平均Navier-Stokes解算器EllipSys2D结合e ^N层流-湍流边界层过渡的过渡模型。通过对机翼形状进行直接的几何修改来对配置进行建模。结果表明，最重要的参数是扰动的位置和深度/高度，在指定的迎角和扰动参数范围内，升力减少35％，升力/阻力减少90％。