梯度分布多孔尾缘对翼型低速扰流自噪声的影响

doi:10.3901/JME.2025.17.150

机械工程学报 ›› 2025, Vol. 61 ›› Issue (17): 150-160.doi: 10.3901/JME.2025.17.150

• 机械动力学 • 上一篇

扫码分享

梯度分布多孔尾缘对翼型低速扰流自噪声的影响

郭鹏^1,2, 冯和英¹, 王勇², 彭叶辉¹, 崔盼望^1,2, 余荣科^1,2

1. 湖南科技大学机械设备健康维护湖南省重点实验室湘潭 411201;
2. 中国空气动力研究与发展中心气动噪声控制重点实验室绵阳 621000

收稿日期:2024-09-12 修回日期:2025-03-19 发布日期:2025-10-24
作者简介:郭鹏，男，1999年出生。主要从事气动声学方面的研究。E-mail：18296670535@163.com;冯和英(通信作者)，女，1983年出生，博士，教授。主要从事气动噪声预测及控制方面的研究。E-mail：fengheying@hnust.edu.cn
基金资助:
国家自然科学基金(12261131502, 52375090)和湖南省自然科学基金(2022JJ30249)资助项目。

Research on the Influence of Gradient Distribution Porous Trailing Edge on Airfoil Self Noise

GUO Peng^1,2, FENG Heying¹, WANG Yong², PENG Yehui¹, CUI Panwang^1,2, YU Rongke^1,2

1. Hunan Provincial Key Laboratory of Health Maintenance for Mechanical Equipment, Hunan University of Science and Technology, Xiangtan 411201;
2. Key Laboratory of Aerodynamic Noise Control, China Aerodynamics Research and Development Center, Mianyang 621000

Received:2024-09-12 Revised:2025-03-19 Published:2025-10-24

摘要/Abstract

摘要： 多孔介质已被证明能够用于翼型降噪领域，但对于梯度分布多孔降噪及其降噪机理并不完善，现以NACA0012翼型为基准设计了9种不同组合的多孔尾缘翼型模型，测试并分析不同工况下的翼型噪声特性与降噪机理。研究发现：迎角和来流速度较大时，多孔尾缘的降噪效果更好，梯度分布多孔尾缘降噪峰值可达43.68 dB，总声压级最大降幅可达19.72 dB；多孔尾缘能够抑制翼型自噪声的根源在于其对翼型上表面及尾迹附近流动特征的控制作用，当上下表面压差足够驱动流体穿过多孔介质时，流体会消除翼型上表面流动分离、延缓涡脱落、减少大尺度旋涡、控制尾迹波动、减小逆压梯度和回流区大小、形成稳定的剪切层，从而有效控制各种流动噪声源；相较于均匀分布的多孔尾缘，合适的梯度分布多孔尾缘降噪效果更佳，且能改善气动阻力、提高气动升力。

关键词: 翼型自噪声, 多孔尾缘, 窄带单音, 流动控制

Abstract: Porous media has been proven to be effective in reducing the airfoil noise, but the physical mechanism of the chordwise-varying porous noise reduction and its noise reduction mechanism are not perfect. Nine different types of porous distributions have been designed based on the NACA0012 airfoil, and the scattering characteristics and noise-abatement mechanism of the airfoil under different operating conditions have been investigated and analyzed. The results demonstrate that when the angle of attack and incoming flow velocity are large, the noise reduction effect of the gradient porous trailing edge is better, with a peak noise reduction of 43.68 dB and a maximum total sound pressure level reduction of 19.72 dB. These phenomenon root in the control over the flow characteristics on the upper surface and near the wake. When the pressure difference between the upper and lower surfaces is sufficient to drive the fluid through the porous medium, the fluid will manipulate the flow separation on the upper surface of the airfoil, delay the vortex shedding, reduce the large-scale vortices, control the wake fluctuations, reduce the reverse pressure gradient and reflux zone size, and form a stable shear layer, thus effectively controlling the flow-induced noise sources. Compared to uniformly distributed porous trailing edges, a suitable gradient distributed porous trailing edge can reduce the noise more significantly and can improve the aerodynamic drag and lift.

Key words: airfoil self-noise, porous trailing edge, narrow band single tone, flow control

中图分类号:

V211

郭鹏, 冯和英, 王勇, 彭叶辉, 崔盼望, 余荣科. 梯度分布多孔尾缘对翼型低速扰流自噪声的影响[J]. 机械工程学报, 2025, 61(17): 150-160.

GUO Peng, FENG Heying, WANG Yong, PENG Yehui, CUI Panwang, YU Rongke. Research on the Influence of Gradient Distribution Porous Trailing Edge on Airfoil Self Noise[J]. Journal of Mechanical Engineering, 2025, 61(17): 150-160.

参考文献

[1] 乔渭阳, 仝帆, 陈伟杰, 等. 仿生学气动噪声控制研究的历史、现状和进展[J]. 空气动力学学报, 2018, 36(1): 98-121. QIAO Weiyang, TONG Fan, CHEN Weijie, et al. Review on aerodynamic noise reduction with bionic configuration[J]. Acta Aerodynamica Sinica. 2018, 36(1): 98-121.
[2] AIHARA A, BOLIN K, GOUDE A, et al. Aeroacoustic noise prediction of a vertical axis wind turbine using large eddy simulation[J]. International Journal of Aeroacoustics, 2021, 20(8): 959-978.
[3] LI Dian, LIU Xiaomin, HU Fujia, et al. Effect of trailing-edge serrations on noise reduction in a coupled bionic aerofoil inspired by barn owls[J]. Bioinspiration & Biomimetics, 2019, 15(1): 016009.
[4] WANG Yong, ZHAO Kun, LU Xiangyu, et al. Bio-inspired aerodynamic noise control: A bibliographic review[J]. Applied Sciences, 2019, 9(11): 2224.
[5] JAWORSKI J W, PEAKE N. Aeroacoustics of silent owl flight[J]. Annual Review of Fluid Mechanics, 2020, 52: 395-420.
[6] 刘汉儒, 陈南树, 刘宇, 等. 多孔介质流动控制及气动降噪研究进展[J]. 航空学报, 2023, 44: 027923. LIU Hanru, CHEN Nanshu, LIU Yu, et al. Review of porous media using in flow control and aerodynamic noise reduction[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44: 027923(in Chinese).
[7] 王勇, 郝南松, 赖庆仁, 等. 多孔前缘抑制圆柱-翼型干涉噪声实验[J]. 航空动力学报, 2022, 37(9): 1807-1814. WANG Yong, HAO Nansong, LAI Qingren, et al. Experiment of rod-airfoil interaction noise reduction using porous leading edges[J]. Journal of Aerospace Power, 2022, 37(9): 1807-1814.
[8] ZHOU Peng, ZHONG Siyang, ZHANG Xin. On the effect of velvet structures on trailing edge noise: Experimental investigation and theoretical analysis[J]. Journal of Fluid Mechanics, 2021, 919: A11.
[9] LIU Yu, DOWLING A P. Assessment of the contribution of surface roughness to airframe noise[J]. AIAA Journal, 2007, 45(4): 855-869.
[10] 刘汉儒, 陈南树. 多孔渗透结构影响尾缘噪声的试验[J]. 航空学报, 2017, 38(6): 120746. LIU Hanru, CHEN Nanshu. Test on effects of porous permeable section on trailing edge noise[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(6): 120746.
[11] FASSMANN B W, RAUTMANN C, EWERT R, et al. Prediction of porous trailing edge noise reduction via acoustic perturbation equations and volume averaging[C]//21st AIAA/CEAS Aeroacoustics Conference. 2015: 2525.
[12] 杨成浩, 冯和英, 彭叶辉, 等. 多孔介质对圆柱-翼型干涉噪声的影响[J]. 航空动力学报, 2022, 37(7): 1528-1538. YANG Chenghao, FENG Heying, PENG Yehui, et al. Effects of porous media on rod-airfoil interaction noise[J]. Journal of Aerospace Power, 2022, 37(7): 1528-1538.
[13] WANG Yong, TONG Fan, CHEN Zhengwu, et al. Rod-airfoil interaction noise reduction using gradient distributed porous leading edges[J]. Applied Sciences, 2022, 12(10): 4941.
[14] ALI S A S, AZARPEYVAND M, DA SILVA C R I. Trailing-edge flow and noise control using porous treatments[J]. Journal of Fluid Mechanics, 2018, 850: 83-119.
[15] ALI S A S, AZARPEYVAND M, DA SILVA C R I. Trailing edge bluntness noise reduction using porous treatments[J]. Journal of Sound and Vibration, 2020, 474: 115257.
[16] GEYER T F, SARRADJ E, FRITZSCHE C. Measurement of the noise generation at the trailing edge of porous airfoils[J]. Experiments in Fluids, 2010, 48: 291-308.
[17] GEYER T F, SARRADJ E. Trailing edge noise of partially porous airfoils[C]//20th AIAA/CEAS Aeroacoustics Conference. 2014: 3039.
[18] BOWEN L, CELIK A, AZARPEYVAND M, et al. On the use of tailored permeable surfaces for turbulence interaction noise control[C]//AIAA Aviation 2020 Forum. 2020: 2530.
[19] CARPIO A R, MARTINEZ R M, AVALLONE F, et al. Experimental characterization of the turbulent boundary layer over a porous trailing edge for noise abatement[J]. Journal of Sound and Vibration, 2019, 443: 537-558.
[20] RUBIO CARPIO A, AVALLONE F, RAGNI D, et al. Mechanisms of broadband noise generation on metal foam edges[J]. Physics of Fluids, 2019, 31(10): 105110.
[21] 刘汉儒, 王掩刚, 张俊. 尾缘多孔结构流动控制影响的数值研究[J]. 西北工业大学学报, 2017, 35(1): 103-108. LIU Hanru, WANG Yangang, ZHANG Jun. Numerical simulation of the effects of porous-trailing-edge on flow control[J]. Journal of Northwestern Polytechnical University, 2017, 35(1): 103-108.
[22] WANG Yong, HAO Nansong, LU Xiangyu, et al. Airfoil self-noise reduction by gradient distributed porous trailing edges[J]. Journal of Aerospace Engineering, 2021, 34(6): 04021075.
[23] LADSON C L, HILL A S, JOHNSON JR W G. Pressure distributions from high Reynolds number transonic tests of an NACA 0012 airfoil in the Langley 0.3-meter transonic cryogenic tunnel[R]. Hampton, VA: National Aeronautics and Space Administration, Langley Research Center, 1987.
[24] SEO J H, MOON Y J. Aerodynamic noise prediction for long-span bodies[J]. Journal of Sound and Vibration, 2007, 306(3-5): 564-579.
[25] BOWEN L, CELIK A, AZARPEYVAND M, et al. Porous geometry effects on the generation of turbulence interaction noise[C]//AIAA AVIATION 2021 FORUM. 2021: 2193.
[26] TERUNA C, MANEGAR F, AVALLONE F, et al. Noise reduction mechanisms of an open-cell metal-foam trailing edge[J]. Journal of Fluid Mechanics, 2020, 898: A18.
[27] CARPIO A R, AVALLONE F, RAGNI D, et al. Quantitative criteria to design optimal permeable trailing edges for noise abatement[J]. Journal of Sound and Vibration, 2020, 485: 115596.
[28] ZHANG Minghui, CHONG T P. Experimental investigation of the impact of porous parameters on trailing-edge noise[J]. Journal of Sound and Vibration, 2020, 489: 115694.
[29] BAE Y, MOON Y J. Effect of passive porous surface on the trailing-edge noise[J]. Physics of Fluids, 2011, 23(12): 126101.
[30] ZAMPONI R, VAN DE WYER N, SCHRAM C F. Experimental investigation of airfoil turbulence-impingement noise reduction using porous treatment[C]//25th AIAA/CEAS Aeroacoustics Conference. 2019: 2649.

梯度分布多孔尾缘对翼型低速扰流自噪声的影响

Research on the Influence of Gradient Distribution Porous Trailing Edge on Airfoil Self Noise

PDF

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 10

编辑推荐

Metrics

本文评价

[1]	冯俊鑫, 赵振宙, 陈明, 江瑞芳, 王丁丁, 刘一格. 涡流发生器高度对风力机翼段动态失速过程的影响分析[J]. 机械工程学报, 2024, 60(8): 291-298.
[2]	郭广强, 李瑞安, 张人会, 陈学炳, 王静宜. 不同工况下液环泵轴向叶顶间隙泄漏流的等离子体激励调控研究[J]. 机械工程学报, 2024, 60(22): 447-456.
[3]	庞可超, 黄典贵. 双层翼叶片几何参数对水平轴风力机气动性能影响研究[J]. 机械工程学报, 2023, 59(2): 259-267.
[4]	孙朱俊, 许斌, 黄典贵. 前缘涡振圆柱对翼型气动性能的影响[J]. 机械工程学报, 2022, 58(6): 242-252.
[5]	张强, 缪维跑, 李春, 张万福. 喷管式翼缝对垂直轴风力机气动性能影响研究[J]. 机械工程学报, 2021, 57(22): 335-343.
[6]	丁叁叁, 姚拴宝, 陈大伟. 高速磁浮列车气动升力特性[J]. 机械工程学报, 2020, 56(8): 228-234.
[7]	朱建勇, 刘沛清. 180°螺旋式Savonius风力机气动特性试验研究[J]. 机械工程学报, 2020, 56(8): 155-161.
[8]	张振辉, 李栋. 合成射流激励器的特性及其后台阶流动控制应用[J]. 机械工程学报, 2018, 54(6): 224-232.
[9]	朱建勇, 阳尧, 陈权, 刘沛清. 绊线对H型风轮启动特性的影响[J]. 机械工程学报, 2018, 54(20): 115-122.
[10]	李凌丰;刘际轩;茅旭飞. 螺杆加工塑料时熔体流动的数值模拟[J]. , 2011, 47(24): 50-56.