Parametric influence numerical simulation study on blade serrations for noise reduction

XIE Xinglong; ZHU Qinghua; QIAO Moheng; JIANG Junjie

doi:10.16615/j.cnki.1674-8190.2026.03.15

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Parametric influence numerical simulation study on blade serrations for noise reduction

Special Column of 41th China Helicopter Academic Exchange Conference | 更新时间：2026-06-16

- Parametric influence numerical simulation study on blade serrations for noise reduction
- Advances in Aeronautical Science and Engineering Vol. 17, Issue 3, Pages: 144-154(2026)
- 作者机构：
  
  南京航空航天大学直升机动力学全国重点实验室/直升机研究院，南京 210016
- 作者简介：
- 基金信息：
- DOI：10.16615/j.cnki.1674-8190.2026.03.15
  CLC： V279;V211.52
- Received：14 October 2025，
  
  Revised：2026-03-20，
  
  Published：28 June 2026
- 稿件说明：
移动端阅览
谢兴隆, 朱清华, 乔墨恒, 等. 桨叶锯齿降噪参数化影响数值模拟研究[J]. 航空工程进展, 2026, 17(3): 144-154.

XIE Xinglong, ZHU Qinghua, QIAO Moheng, et al. Parametric influence numerical simulation study on blade serrations for noise reduction[J]. Advances in Aeronautical Science and Engineering, 2026, 17(3): 144-154.(in Chinese)
谢兴隆, 朱清华, 乔墨恒, 等. 桨叶锯齿降噪参数化影响数值模拟研究[J]. 航空工程进展, 2026, 17(3): 144-154. DOI： 10.16615/j.cnki.1674-8190.2026.03.15.

XIE Xinglong, ZHU Qinghua, QIAO Moheng, et al. Parametric influence numerical simulation study on blade serrations for noise reduction[J]. Advances in Aeronautical Science and Engineering, 2026, 17(3): 144-154.(in Chinese) DOI： 10.16615/j.cnki.1674-8190.2026.03.15.

摘要

目前多旋翼无人机旋翼存在严重的噪声问题。为降低旋翼噪声，基于仿生学原理，研究后缘锯齿结构对旋翼气动噪声的影响及降噪机理。以一款变弦长双桨叶旋翼为基准模型，通过向内切割桨叶后缘设计7种不同锯齿高度（

）和宽度（

）参数的锯齿桨叶；采用计算流体力学（CFD）方法，结合滑移网格技术模拟悬停流场，并应用分离涡模拟（DES）与非定常流场数据，求解FW-H方程预测桨尖平面和桨轴平面噪声。结果表明：后缘锯齿结构能有效降低旋翼噪声，较大的锯齿高度会过度减小桨叶升力面积，严重影响桨叶的气动性能，较宽的锯齿宽度不利于锯齿打碎大涡结构，不利于中高频噪声的抑制，需要寻求合适的齿高比以评估桨叶的综合性能；综合考虑气动性能与降噪效果，锯齿参数为

10的桨叶表现最优，其悬停效率与原桨叶相当，总声压级相比原桨叶降低约1.2 dB。

Abstract

At present， the rotors of multi-rotor drones have serious noise problems. This study investigates the influence and noise reduction mechanism of trailing-edge serrations on rotor aerodynamic noise based on bionics principles. Using a variable-chord-length dual-blade rotor as the baseline model， seven serrated blades with different serration height （

） and width （

） parameters are designed by inwardly cutting the trailing edge of the blades. The computational fluid dynamics （CFD） method， combined with sliding mesh technology， is employed to simulate the hover flow field. Detached eddy simulation （DES） and unsteady flow field data are u

tilized to solve the FW-H equations for predicting noise on the rotor tip plane and rotor shaft plane. The research results indicate that trailing-edge serrations can effectively reduce rotor noise. However， larger serration heights excessively reduce the blade lift area， significantly impairing aerodynamic performance. Wider serration widths are less effective at breaking down large vortex structures， hindering mid-to-high frequency noise suppression. Therefore， seeking an appropriate tooth height ratio is crucial for evaluating the comprehensive performance of the blade. Considering both aerodynamic performance and noise reduction effectiveness， the blade with serration parameters

10 demonstrated optimal performance. Its hover efficiency is comparable to the original blade， while the overall sound pressure level （OASPL） is reduced by approximately 1.2 dB compared to the original blade.

关键词

Keywords

references

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