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声是许多生理和心理影响的原因。世界卫生组织在2011年估计，由于暴露于高水平的噪音，西欧国家每年在西欧国家每年损失多达160万个健康的人生年。这是直接冲突，欧盟和美国的航班数量进一步增加，以及进一步的岸上风电场。因此，至关重要的是要更好地了解来自不同空气组件的噪声机制并开发量身定制的降噪方法，以减少源噪声。在所有组件中，由于它对飞机或风力涡轮机的整体噪声做出了贡献，因此对航空层产生噪声的理解非常重要。在很大程度上，我们目前对空气噪声产生的了解仅限于以低攻击角度进行的驾驶。但是，大多数航空翼型以较高的攻击角度运行，以最大程度地发挥空气动力学性能，它们容易分离和失速，尤其是在各种条件下运行时。在这些情况下，与较低的攻击角度相比，噪声产生以及流动机制大不相同。我们对机制以及预测这些噪声源的能力的知识和理解是有限的。这个合作项目包括工业伙伴的贡献，旨在在分离和失速的情况下对噪声产生机制发展新的理解。目的是执行实验和数值模拟，以在广泛的操作条件下建立一个高保真数据库的流量和噪声数据库。然后，数据将用于识别在高攻击角度以不同的气压噪声源有助于不同的流动机制。实验数据和数值数据还将用于开发新的噪声预测的全面验证模型，然后我们的工业伙伴（GE-Dowty和Embaer）可以使用它们来改善不同应用程序跨不同应用的下一代提升表面的设计。总体而言，该项目将使我们对整个政权的噪声产生机制的理解有所改变，并为更准确的噪声预测和潜在降解策略的发展铺平道路。

项目成果

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: 10.2514/6.2021-2263
• 发表时间: 2021
• 作者: Gstrein F

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: 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

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: 10.2514/6.2021-2538
• 发表时间: 2021
• 作者: Chen G

Improving Accuracy of Airfoil Trailing Edge Noise Models with Turbulent Flow Anisotropy

利用湍流各向异性提高翼型后缘噪声模型的精度

• DOI: 10.2514/6.2022-3105
• 发表时间: 2022
• 作者: Abid H

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: 10.2514/6.2020-2580
• 发表时间: 2020
• 作者: Kamliya Jawahar H