Effect of Separation and Stall on Aerofoil Noise

分离和失速对机翼噪声的影响

• 批准号: EP/R010846/1
• 负责人: Mahdi Azarpeyvand
• 金额: $ 55.35万
• 依托单位: University of Bristol
• 依托单位国家: 英国
• 项目类别: Research Grant
• 财政年份: 2018
• 资助国家: 英国
• 起止时间: 2018 至 无数据
• 项目状态: 已结题
• 来源: https://gtr.ukri.org/projects?ref=EP%2FR010846%2F1
• 关键词: Effect; Separation; Stall; Aerofoil; Noise

It is well established that long-term exposure to aircraft and wind turbine noise is responsible for many physiological and psychological effects. The World Health Organization estimated in 2011 that up to 1.6 million healthy life years are lost annually in the western European countries because of exposure to high levels of noise. This is in direct conflict with the further increase in the number of flights in the EU and US and development and further expansion of on-shore wind farms. Therefore, it is critical to better understand the noise generation mechanism from different aero-components and develop tailored noise reduction methods in order to reduce the noise at source. Amongst all components, understanding of noise generation from aerofoils is of great importance, due to its contribution to the overall noise of aircraft or wind turbine. To a great extent, our current knowledge of aerofoil noise generation is limited to aerofoils at low angles of attack. However, most aerofoils are operated at higher angles of attack to maximise aerodynamic performance where they are prone to separation and stall, especially when they are operating under varied conditions. In these situations, the noise generation as well as the flow mechanisms are substantially different compared to lower angles of attack. Our knowledge and understanding of the mechanisms as well as our ability to predict these noise sources is limited. This collaborative project, which includes contributions from industrial partners, aims to develop new understanding of noise generation mechanisms in the presence of separation and stall. The goal is to perform experiments and numerical simulations in order to establish a high-fidelity database of flow and noise for over a wide range of operating conditions. The data will then be used to identify flow mechanisms that contribute to the different aerofoil noise sources at high angles of attack. The experimental and numerical data will also be utilised to develop new fully-validated models for noise prediction, which can then be used by our industrial partners (GE-Dowty and Embraer) to improve the design of next generation of lifting surfaces across different applications. Overall, this project will bring about a step change in our understanding of noise generation mechanisms across the entire regime and pave the way to more accurate noise predictions and development of potential noise mitigation strategies.

众所周知，长期接触飞机和风力涡轮机噪音会造成许多生理和心理影响。世界卫生组织 2011 年估计，西欧国家每年因暴露于高强度噪音而损失多达 160 万健康生命年。这与欧盟、美国航班数量的进一步增加以及陆上风电场的开发和进一步扩建产生了直接冲突。因此，更好地了解不同航空部件的噪声产生机制并开发定制的降噪方法以从源头上降低噪声至关重要。在所有部件中，了解机翼产生的噪声非常重要，因为它对飞机或风力涡轮机的整体噪声有影响。在很大程度上，我们目前对翼型噪声产生的了解仅限于低迎角的翼型。然而，大多数机翼都在较高的迎角下运行，以最大限度地提高空气动力性能，但在这种情况下，它们很容易分离和失速，特别是当它们在不同的条件下运行时。在这些情况下，噪声的产生以及流动机制与较低攻角相比有很大不同。我们对机制的了解和理解以及预测这些噪声源的能力是有限的。该合作项目包括工业合作伙伴的贡献，旨在加深对分离和失速情况下噪声产生机制的新理解。目标是进行实验和数值模拟，以便建立适用于各种操作条件的高保真流量和噪声数据库。然后，这些数据将用于识别在高攻角下造成不同机翼噪声源的流动机制。实验和数值数据还将用于开发新的完全验证的噪声预测模型，然后我们的工业合作伙伴（GE-Dowty 和 Embraer）可以使用该模型来改进跨不同应用的下一代升力面的设计。总体而言，该项目将使我们对整个体系中噪声产生机制的理解发生重大变化，并为更准确的噪声预测和开发潜在的噪声缓解策略铺平道路。

项目成果

Control of Wake-Airfoil Interaction Noise Using Slotted-sawtooth Trailing-edge Serrations

使用开槽锯齿后缘锯齿控制尾流翼型相互作用噪声

• DOI: http://dx.10.2514/6.2020-2517
• 发表时间: 2020
• 作者: Liu X

Aerodynamic and Aeroacoustic Performance of Spanwise Morphed Airfoils

展向变形翼型的气动和气动声学性能

• DOI: http://dx.10.2514/6.2020-2580
• 发表时间: 2020
• 作者: Kamliya Jawahar H

Wake-aerofoil interaction noise control with trailing-edge serrations

利用后缘锯齿进行尾流机翼相互作用噪声控制

• DOI: http://dx.10.1016/j.expthermflusci.2021.110510
• 发表时间: 2022
• 期刊: Experimental Thermal and Fluid Science
• 影响因子: 3.2
• 作者: Liu X

Investigations on the Application of Various Surface Treatments for Trailing Edge Noise Reduction on a Flat Plate

平板后缘降噪各种表面处理应用的研究

• DOI: http://dx.10.2514/6.2021-2263
• 发表时间: 2021
• 作者: Gstrein F

The effect of spanwise length on the near-field dynamics of flow past a cylinder using Large-Eddy Simulation

使用大涡模拟研究展向长度对流过圆柱体的近场动力学的影响

• DOI: http://dx.10.2514/6.2021-2538
• 发表时间: 2021
• 作者: Chen G