Three airfoil models with bionic micro-grooves were developed to investigate the effect of the bionic micro-grooves on the airfoil flow field and aerodynamic performance. Large eddy simulation (LES) was used to predict the flow field around the airfoil. The Re were 1.6 x 10(5) and 2 x 10(5), and the angle of attack was 6 degrees. The results show that all three airfoils reduce the velocity gradient at the airfoil suction surface near the wall and the energy loss in the boundary layer. The area of the recirculation zone of the H1 and H2 airfoils is significantly reduced. However, when the Re is 1.6 x 10(5), the area of the recirculation zone of the H3 airfoil increases. The aerodynamic performance of all three airfoils was improved. When the Re is 1.6 x 10(5), the aerodynamic performance of the H1 airfoil is improved most significantly, and the drag reduction rate reaches 16.41. When the Re is 2 x 10(5), the aerodynamic performance improvement of H2 is the most obvious, and the drag reduction rate reaches 17.45. In order to achieve the best drag reduction effect, the position of the bionic micro-grooves should gradually approach the wing's tail with the increase of Re.
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机译：开发了3种带有仿生微槽的翼型模型，以研究仿生微槽对翼型流场和空气动力学性能的影响。采用大涡模拟（LES）预测翼型周围的流场。Re 为 1.6 x 10（5） 和 2 x 10（5），迎角为 6 度。结果表明：3种翼型均减小了翼型吸壁面的速度梯度和边界层的能量损失;H1 和 H2 翼型的再循环区面积显着减小。但是，当 Re 为 1.6 x 10（5） 时，H3 翼型的再循环区面积增加。所有三个翼型的空气动力学性能都得到了改善。当Re为1.6×10（5）时，H1翼型的空气动力学性能得到最显著的改善，减阻率达到16.41%。当Re为2×10（5）时，H2的空气动力学性能提升最为明显，减阻率达到17.45%。为了达到最佳的减阻效果，仿生微槽的位置应随着Re的增加逐渐接近机翼尾部。
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