Study of the Empirical Turbulent Boundary Layer Models for Aircraft Cabin Noise Prediction

飞机座舱噪声预测的经验湍流边界层模型研究

• 批准号: 459295-2013
• 负责人: Rocha, Joana
• 金额: $ 1.82万
• 依托单位: Carleton University
• 依托单位国家: 加拿大
• 项目类别: Engage Grants Program
• 财政年份: 2013
• 资助国家: 加拿大
• 起止时间: 2013-01-01 至 2014-12-31
• 项目状态: 已结题
• 来源: https://www.nserc-crsng.gc.ca/ase-oro/Details-Detailles_eng.asp?id=542220
• 关键词: Study; Empirical; Turbulent; Boundary; Layer

High levels of noise and vibration in aircraft cabin, experienced during flight, are associated with negative effects in human health and overall flight comfort. This problem becomes even more significant during long flights, affecting crew and passengers. In the past few years, the level of interest in aircraft cabin noise and vibration research has increased. The main cause for this interest is related to the fact that increased cruise flight speeds have resulted in higher levels of aircraft cabin noise during cruise. Additionally, as novel aircraft designs are being considered, cabin noise will need to be addressed in the early phases of the design process. New materials are progressively being more applied in aircraft structures for reduced weight, which will also impact aircraft cabin noise and vibration levels. As such, the need for better understanding and predicting aircraft interior noise has increased, as well as the interest in the development and design of better noise reduction techniques. During cruise flight of a typical passengers' aircraft, the turbulent boundary layer (TBL), developed over the external fuselage skin, represents the major source of cabin noise. Being of random nature, the TBL wall pressure distribution is usually mathematically described through empirical models. Even though several empirical models exist to provide the TBL wall pressure distribution, all the models provide dissimilar predictions, and therefore, the empirical description of the TBL excitation remains and ongoing topic of research. Considering this problem, the present proposal aims to investigate the TBL wall pressure fluctuations developed over the surface of a panel tested in wind tunnel. Experimental results obtained will subsequently be compared with the predicted data obtained through empirical models, allowing the identification of which model(s) better matches the wind tunnel measurements.

飞行期间机舱内的高水平噪声和振动与人体健康和整体飞行舒适性的负面影响有关。这个问题在长途飞行中变得更加严重，影响机组人员和乘客。在过去的几年里，人们对飞机座舱噪声和振动研究的兴趣不断增加。这种兴趣的主要原因与巡航飞行速度增加导致巡航期间飞机机舱噪声水平更高的事实有关。此外，由于正在考虑新的飞机设计，机舱噪声将需要在设计过程的早期阶段加以解决。新材料正逐步更多地应用于飞机结构中以减轻重量，这也将影响飞机机舱噪音和振动水平。因此，对更好地理解和预测飞机内部噪声的需求已经增加，以及对开发和设计更好的降噪技术的兴趣也在增加。在典型客机的巡航飞行过程中，在机身外蒙皮上形成的湍流边界层（TBL）是机舱噪声的主要来源。由于具有随机性，TBL壁压分布通常通过经验模型进行数学描述。尽管存在几种经验模型来提供TBL壁压分布，但所有模型提供不同的预测，因此，TBL激励的经验描述仍然是正在进行的研究主题。考虑到这一问题，本文的目的是研究在风洞中试验的壁板表面上产生的TBL壁压脉动。随后将获得的实验结果与通过经验模型获得的预测数据进行比较，以确定哪种模型更好地匹配风洞测量。