Study on Effect of Airfoil with Cracked Trailing Edge on Aerodynamic Performance and Static Structure

吕昌睿; 叶学民; 乔晨; 李春曦

doi:10.19805/j.cnki.jcspe.2025.240366

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Study on Effect of Airfoil with Cracked Trailing Edge on Aerodynamic Performance and Static Structure

更新时间：2026-10-10

- Study on Effect of Airfoil with Cracked Trailing Edge on Aerodynamic Performance and Static Structure
- Chinese Journal of Power Engineering Vol. 45, Issue 7, Pages: 1028-1036(2025)
- 作者机构：
  
  华北电力大学河北省低碳高效发电技术重点实验室,河北,保定,071003
- 作者简介：
- 基金信息：
- DOI：10.19805/j.cnki.jcspe.2025.240366
  CLC：
- Online First：14 July 2025，
  
  Published：2025
- 稿件说明：
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吕昌睿,叶学民,乔晨,李春曦. 尾缘开裂对翼型气动性能及静力结构的影响研究动力工程学报, 2025, 45(7): 1028-1036 https://doi.

org/10.19805/j.cnki.jcspe.2025.240366
吕昌睿,叶学民,乔晨,李春曦. 尾缘开裂对翼型气动性能及静力结构的影响研究动力工程学报, 2025, 45(7): 1028-1036 https://doi. DOI： 10.19805/j.cnki.jcspe.2025.240366.

org/10.19805/j.cnki.jcspe.2025.240366 DOI：

摘要

为探究风力机叶片翼型尾缘开裂对翼型气动性能及静力结构的影响

以S809翼型为研究对象

分析了尾缘开裂高度和深度对翼型气动参数及内流特征的影响

探讨了翼型尾缘等效应力及振动特性的变化。结果表明:翼型失速前

尾缘开裂后翼型的气动性能远低于原翼型

且开裂高度对翼型气动性能的影响大

而开裂深度的影响很小

但开裂深度对翼型静力结构的影响要大于开裂高度的影响;尾缘开裂高度增大

改变了翼型尾缘气动外形

导致失速前翼型的气动性能大幅下降

但失速后气动性能略微提高;增加开裂深度

使得翼型尾缘厚度增加

与较小开裂深度翼型相比

气动性能小幅提升;尾缘开裂后

增大了尾缘等效应力

且在固有频率范围内发生共振的概率增大。

Abstract

To investigate the effect of the wind turbine blade airfoil with cracked trailing edge on aerodynamic performance and static structure

the effects of the height and depth of trailing edge cracking on aerodynamic parameters and internal flow of the S809 airfoil were analyzed

and the changes in airfoil equivalent stress and vibration characteristics were examined. Results show that before the airfoil stalls

the aerodynamic performance of the airfoil with cracked trailing edge is much lower than that of the original one

and the cracked height has a significant impact on the aerodynamic performance while the cracked depth has little effect. However

the impact of cracked depth on the static structure of the airfoil is more notable than the cracked height. The increase in cracked height alters the aerodynamic shape of the trailing edge

thereby leading to a significant reduction in the aerodynamic performance of the airfoil before the stall but a slight increment after the stall. The trailing edge thickness increases with increasing cracked depth

resulting in a slight improvement of the aerodynamic performance compared with the airfoil with smaller cracked depth. After the trailing edge cracks

the equivalent stress of the trailing edge increases and the risk of resonance in the natural frequency range is promoted.

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references

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