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

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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.