The optimization of the airfoil has a significant impact on the reduction of energy consumption for a rotary machine. In this paper, ANSYS Fluent is used to study the influence of different groove structure sizes on the turbulence drag of NACA0012 airfoil blades, and the drag reduction mechanism is analyzed. The results show that the groove structure can significantly reduce the drag during the working speed of the fan. The optimal groove size is s = 0.1 mm and the drag is reduced by 9.65%. The secondary vortices reduce the normal velocity gradient at the top of the groove structure, resulting in a reduction in viscous drag. However, as the groove size increases, the drag reduction effect decreases, and even the drag increases. The overall shear stress of the airfoil surface with the transverse groove structure is smaller than the original airfoil, and the velocity gradient of the airfoil surface is reduced. The two sides work together to reduce the turbulence drag of the airfoil. Besides, the spacing between the grooves increases the shear stress in some areas, but reduces the mutual interference of the vortices, so there is an optimum value for the groove spacing.

机翼的优化对降低旋转机械的能耗有重大影响。本文利用ANSYS Fluent软件研究了不同沟槽结构尺寸对NACA0012翼型叶片湍流阻力的影响，并分析了减阻机理。结果表明，沟槽结构可以显着降低风扇工作速度期间的阻力。最佳凹槽尺寸为s = 0.1 mm，阻力减小了9.65％。次级涡流降低了凹槽结构顶部的法向速度梯度，从而降低了粘性阻力。但是，随着槽尺寸的增大，减阻效果减小，甚至阻力增大。具有横向沟槽结构的机翼表面的总剪切应力小于原始机翼，并且减小了机翼表面的速度梯度。双方共同努力，减少了机翼的湍流阻力。此外，凹槽之间的间隔在某些区域增加了剪切应力，但是减小了涡旋的相互干扰，因此凹槽间隔具有最佳值。