凹腔结构对风力机翼型减阻性能影响研究

薛佳乐; 陈永艳; 宋力; 苏昕; 毕金龙

doi:doi:10.19912/j.0254-0096.tynxb.2024-1180

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凹腔结构对风力机翼型减阻性能影响研究

更新时间：2025-12-10

- 凹腔结构对风力机翼型减阻性能影响研究
- Issue 11, Pages: 641-649(2025)
- 作者机构：
- 作者简介：
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- DOI：doi:10.19912/j.0254-0096.tynxb.2024-1180
  CLC： K83
- Published Online：04 December 2025，
  
  Published：04 December 2025
- 稿件说明：
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薛佳乐, 陈永艳, 宋力, et al. 凹腔结构对风力机翼型减阻性能影响研究[J]. 2025, (11): 641-649.
DOI：

薛佳乐, 陈永艳, 宋力, et al. 凹腔结构对风力机翼型减阻性能影响研究[J]. 2025, (11): 641-649. DOI： doi:10.19912/j.0254-0096.tynxb.2024-1180.

摘要

为探究不同凹腔结构对风力机翼型减阻性能影响研究

利用SST湍流模型对设置凹腔的NACA0012翼型进行数值模拟

根据Omega准则分析风力机在攻角13°时边界层轴向速度在法向方向的变化

并分析攻角增加时翼型壁面剪切力的变化和对黏性阻力影响的范围。研究发现

凹腔的起点设置在翼型75%c（c为弦长）处

翼型表面边界层的气流抵抗逆压梯度能力增强

此外凹腔的结构呈现“椭月”状

可更好地与凹腔外部高速气流接触形成涡垫效应

从而降低壁面的黏性阻力

研究还发现在尖速比1.2、1.6和2.0时平均转矩系数分别提高3.88%、3.33和2.26%。

Abstract

In order to study the influence of different cavity structures on the drag reduction performance of wind turbine airfoil

the SST turbulence model was used to numerically simulate the NACA0012 airfoil with cavity

and the change of boundary layer axial velocity in the normal direction at 13° angle of attack was analyzed according to Omega criterion. The variation of the shear force on the airfoil wall and the range of influence on the viscous resistance with the increase of the angle of attack are analyzed. It is found that the starting point of the cavity is set at （chord length） of the airfoil

and the airflow resistance of the boundary layer on the surface of the airfoil is enhanced. In addition

the structure of the cavity presents an “crescent moon” shape

which can better contact the high-speed airflow outside the cavity to form a vortex cushion effect

thus reducing the viscous resistance of the wall. The study also found that the average torque coefficient increased by 3.88%

3.33%

and 2.26% respectively at tip speed ratios of 1.2

1.6

and 2.0.

关键词

Keywords

references

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