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Aircraft noise

About: Aircraft noise is a research topic. Over the lifetime, 3051 publications have been published within this topic receiving 32039 citations.


Papers
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Journal ArticleDOI
TL;DR: In this paper, the annoyance aspect of aircraft noise relates to the quality of the sound reaching communities, and attempts to potentially lower this annoyance by optimizing an air-crane's performance.
Abstract: This paper focuses on the annoyance aspect of aircraft noise, which relates to the quality of the sound reaching communities, and attempts to potentially lower this annoyance by optimizing an aircr...

12 citations

BookDOI
01 Jan 1986
TL;DR: The state of the art in theoretical and numerical models and experimentation on broadband noise propagation from high speed aircraft components such as jets and helicopter blades is detailed in this paper, where attention is given to noise produced by jets, shear layers and turbulence and to the acoustic properties of rotors.
Abstract: The state of the art in theoretical and numerical models and experimentation on broadband noise propagation from high speed aircraft components such as jets and helicopter blades is detailed. Attention is given to noise produced by jets, shear layers and turbulence and to the acoustic properties of rotors. The generation and propagation of acoustic noise are discussed in terms of the evolution of concepts for flow-tone generation to include hydrodynamic instabilities. Consideration is also given to techniques for experimental studies and theoretical models for nonlinear features of acoustic propagation of broadband noise and acoustic propagation in partially-choked or soft-walled ducts.

12 citations

Journal ArticleDOI
TL;DR: A proper orthogonal decomposition in conjunction with a response surface methodology-based surrogate model is used to create a rapid noise assessment model which expands the solution space for noise mitigation strategies which can be evaluated, and therefore can lead to novel solutions which cannot be found with traditional modeling methods.
Abstract: A key enabler for sustainable growth of aviation is the mitigation of adverse environmental effects. One area of concern is community noise exposure at large hub airports serving growing population centers. Traditionally, community noise exposure is computed using noise contours around airports, which requires knowledge of a large dataset pertaining to the air traffic operations at the airport of interest. Due to the underlying variability in real-world aircraft operations, numerous assumptions need to be made which adversely affect the accuracy of the model. Reduced-Order Modeling (ROM) methods provide a new framework for the retention of a large number of these parameters, thus improving model speed and accuracy. In this work, a proper orthogonal decomposition in conjunction with a response surface methodology-based surrogate model is used to create a rapid noise assessment model. Validation is performed against results obtained from the aviation environmental design tool with quantitative error metrics and visual contour comparisons. Obtained results are encouraging and motivate further work in this area with other ROM methods. ROM based models for noise assessment expand the solution space for noise mitigation strategies which can be evaluated, and therefore can lead to novel solutions which cannot be found with traditional modeling methods.

12 citations

Proceedings ArticleDOI
01 Jan 1973
TL;DR: In this article, a TF-34 engine was used to investigate engine and flap interaction noise associated with an externally blown flap STOL powered lift system, and the differences in observed noise were related primarily to nozzle effective exhaust velocity, flap impingement velocity, and noise spectral shape.
Abstract: A highly suppressed TF-34 engine was used to investigate engine and flap interaction noise associated with an externally blown flap STOL powered lift system. Noise, efficiency, and velocity decay characteristics of mixed and separate flow exhaust systems including convergent, co-annular, and lobed designs were determined with the engine operating alone. Noise data were then obtained for several of the exhaust configurations with the engine blowing a wing-flap segment. Noise for both the engine alone and the engine with blown flaps showed substantial differences for the various exhaust configurations tested. The differences in observed noise are related primarily to nozzle effective exhaust velocity, flap impingement velocity, and noise spectral shape.

12 citations

Journal ArticleDOI
TL;DR: In this paper, a hybrid active and passive active noise control system was proposed to increase the noise attenuation transmitted in the propeller aircraft fuselage, and the performance of the hybrid active device was evaluated on the first three blade pass frequencies.
Abstract: Over the years, the interior noise levels have been improved, and nowadays a high acoustical comfort is of major importance for the commercial success of propeller aircraft. The use and development of high vibro-acoustic performance devices and their integration on the primary structure are, therefore, among the most critical topics in the greening of the next generation air transportation. The purpose of this research was properly focused on the analysis of a dynamic control system appointed to increase the noise attenuation transmitted in the propeller aircraft fuselage. Passive and active dynamic devices have been studied and characterized in this work. Simulations and tests performed on the first stage demonstrator structure highlighted how the passive tuned vibration absorber increases the comfort controlling the structural behaviour of the fuselage at the first blade pass frequency. Further improvements of fuselage comfort can be reached using active devices. A conceptual design of a hybrid active device able to act on the first three blade pass frequencies has been outlined. The characterization of the whole active noise control system has been described and its effect on noise reduction in fuselage of propeller aircraft has been evaluated.

12 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
202386
2022103
202152
202051
201980
201878