俯仰波浪前缘叶片动态失速主动控制研究

邹琳; 苗亚博; 柳迪伟; 郭晓宇; 王念

doi:doi:10.19912/j.0254-0096.tynxb.2024-1658

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俯仰波浪前缘叶片动态失速主动控制研究

更新时间：2026-02-06

- 俯仰波浪前缘叶片动态失速主动控制研究
- 俯仰波浪前缘叶片动态失速主动控制研究
- 太阳能学报 2026年47卷第1期页码：674-682
- 作者机构：
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- DOI：doi:10.19912/j.0254-0096.tynxb.2024-1658
  中图分类号： TK83
- 网络首发：2026-02-05，
  
  纸质出版：2026-02-05
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邹琳, 苗亚博, 柳迪伟, 等. 俯仰波浪前缘叶片动态失速主动控制研究[J]. 太阳能学报, 2026,47(1):674-682.

邹琳, 苗亚博, 柳迪伟, et al. 俯仰波浪前缘叶片动态失速主动控制研究[J]. 2026, 47(1): 674-682.
邹琳, 苗亚博, 柳迪伟, 等. 俯仰波浪前缘叶片动态失速主动控制研究[J]. 太阳能学报, 2026,47(1):674-682. DOI： doi:10.19912/j.0254-0096.tynxb.2024-1658.

邹琳, 苗亚博, 柳迪伟, et al. 俯仰波浪前缘叶片动态失速主动控制研究[J]. 2026, 47(1): 674-682. DOI： doi:10.19912/j.0254-0096.tynxb.2024-1658.

摘要

基于滑移网格技术和SST k-ω湍流模型建立等离子体激励下叶片动态失速数值计算模型

研究不同等离子激励参数下俯仰（-5°~25°）NACA0012直叶片及其改型的波浪前缘叶片的升阻力、流动结构及动态失速特性

探索波浪前缘耦合等离子体激励对叶片动态失速的主动控制机理。研究发现：波浪前缘叶片能有效降低叶片俯仰时的升阻力峰值并减小倾覆力矩。耦合等离子体激励后

波浪前缘叶片分离涡加速分离

俯仰转换阶段受力落差减小

升力迟滞回环曲线面积减小约23.9%。且下俯段产生的分离涡尺度明显减小

叶片受力波动更小

波浪前缘叶片耦合失速控制效果明显优于直叶片。随着等离子体激励电压幅值的增加

下俯转换时耦合控制作用变强

叶片迟滞效应进一步减小

震荡特性减弱

可有效改善波浪前缘叶片动态失速性能。

Abstract

A numerical model for dynamic stall of the pitching wavy leading-edge blade under plasma excitation was established by employing the sliding mesh technique and SST - turbulence model. The lift and drag

flow structures

and dynamic stall characteristics of pitching （-5°—25°） NACA0012 straight blade and its modified wavy leading-edge blades under different plasma excitation parameters were studied

and the active control mechanism of dynamic stall of the blade with wavy leading-edge blade coupled with plasma excitation was explored. The results show that the wavy leading-edge blade can effectively reduce the peak lift and drag forces and decrease the overturning moment during pitching. After coupling with plasma excitation

the separation vortex of the wavy leading-edge blade separates earlier

and the force drop is reduced during the pitching transition

the area of the lift hysteresis loop is reduced by 23.9%. And the separation vortex generated in the subsequent down-pitching stage is significantly reduced

resulting in smaller force fluctuations

indicating that its controlled performance is superior to that of straight blade. As the plasma excitation voltage amplitude increases

the coupled control effect becomes stronger during the down-pitching transition

further reducing the hysteresis effect of the blade and weakening the oscillation characteristics

effectively improving the dynamic stall performance of the wavy leading-edge blade.

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references

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