Noise due to turbulent flow past a trailing edge

Amiet, R. K.

doi:10.1016/0022-460x(76)90948-2

Cited by 807 publications

(581 citation statements)

References 19 publications

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“…The diffraction of the boundary layer turbulent vortices by the trailing edge is modelled using the isolated flat plate airfoil theory from Amiet 8,9 enhanced by Roger and Moreau 35 to account for skewed gusts. Rotating dipoles are then used to compute the radiated noise field according to Ffowcs-Williams-Hawking theory 15 with an approach similar to Kim and George 18 , however fully accounting for the non-compactness of the sources.…”

Section: A Trailing Edge Noisementioning

confidence: 99%

“…However, they approximated the unsteady blade loading along the chord as a point force. This simplification was enhanced later by Zhou and Joseph 33 (2004) for open propellers using Amiet's isolated airfoil response function 8,9 extended to take into account the contribution of skewed gusts, and then extended by Blandeau 3 for contra-rotating open rotors. A significant contribution for the trailing edge noise prediction was achieved by Roger and Moreau 35 , who introduced a correction for the back-scattering of the leading edge.…”

Section: Introductionmentioning

confidence: 99%

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Prediction of Contra-Rotating Open Rotor broadband noise in isolated and installed configurations

Nodé-Langlois

Wlassow

Languille

et al. 2014

20th AIAA/CEAS Aeroacoustics Conference

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Broadband noise is a significant part of the noise emitted by contra-rotating open rotors. Several noise sources can contribute to the total broadband sound field, with the most dominant ones probably being trailing edge noise, rotor-wake interaction noise and pylon-wake interaction noise. This paper addresses the prediction of these noise sources using analytical models based on Amiet's flat plate airfoil theory and also to empirical turbulence models, fed by input data extracted from steady and unsteady CFD RANS simulations. The models are assessed against wind tunnel tests of Rolls-Royce's rig 145 (build 1) conducted at the DNW anechoic open jet test facility using Rolls-Royce blades and Airbus pylons. The study showed promising results in terms of the ability of the models to predict acoustic power spectrum shapes, peak frequencies and absolute levels. The effects of changes in thrust on broadband wake-interaction noise are well reproduced. However, the models significantly underestimate the effect of thrust on trailing edge noise and the effect of rotational velocity on pylon interaction noise. Nomenclature

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Section: A Trailing Edge Noisementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Prediction of Contra-Rotating Open Rotor broadband noise in isolated and installed configurations

Nodé-Langlois

Wlassow

Languille

et al. 2014

20th AIAA/CEAS Aeroacoustics Conference

View full text Add to dashboard Cite

show abstract

“…The wall normal velocity of turbulent eddies is kinematically blocked by the wall, an effect modelled by the image eddies in the wall of the real turbulence. As the turbulent flow passes over a trailing edge this blocking ends abruptly and provides a site for potentially efficient conversion/scattering of hydrodynamic disturbances into sound [95][96][97]. The turbulent flow approaching the trailing edge and the sound produced by it can be computed using both DNC and hybrid CAA.…”

Section: (I) Slat Noisementioning

confidence: 99%

A second golden age of aeroacoustics?

Lele

Nichols

2014

Phil. Trans. R. Soc. A.

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In 1992, Sir James Lighthill foresaw the dawn of a second golden age in aeroacoustics enabled by computer simulations (Hardin JC, Hussaini MY (eds) 1993 Computational aeroacoustics, New York, NY: Springer (doi:10.1007). This review traces the progress in large-scale computations to resolve the noise-source processes and the methods devised to predict the far-field radiated sound using this information. Keeping focus on aviation-related noise sources a brief account of the progress in simulations of jet noise, fan noise and airframe noise is given highlighting the key technical issues and challenges. The complex geometry of nozzle elements and airframe components as well as the high Reynolds number of target applications require careful assessment of the discretization algorithms on unstructured grids and modelling compromises. High-fidelity simulations with 200-500 million points are not uncommon today and are used to improve scientific understanding of the noise generation process in specific situations. We attempt to discern where the future might take us, especially if exascale computing becomes a reality in 10 years. A pressing question in this context concerns the role of modelling in the coming era. While the sheer scale of the data generated by large-scale simulations will require new methods for data analysis and data visualization, it is our view that suitable theoretical formulations and reduced models will be even more important in future.

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“…The former is similar to the characteristics of trailing edge noise. An early model for this noise was established by Amiet and Howe in the 1970s [4] [5]. Roger and Moreau extended Amiet's trailing edge noise model to the limited chord length model [6] [7]; then, they indicated that the broadband noise in the high-frequency domain is closely related to trailing edge noise.…”

Section: Introductionmentioning

confidence: 99%

Determination of Aerodynamic Sound Sources on Periodicity Noise Generated from a Micro Wind Turbine

Sasaki

Sakada²,

Suzuki³

2014

OJFD

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To discuss the relationship between the periodicity noise and the aerodynamic noise source of a wind turbine, the characteristics of the actual wind turbine were measured by a wind tunnel; moreover, the flow around the impeller immersed in the uniform flow was solved by numerical simulation. In the observed wind turbine, when the mainstream velocity was 7.4 m/s or more, the power coefficient reached maximum at tip speed ratio 8. When the mainstream velocity increased in the driving condition of the maximum power point, the aerodynamic noise increased due to the periodicity noise in the vicinity of 1000 Hz and the broadband noise in the high-frequency domain. The noise sources were concentrated at the leading edge and trailing edge on the suction surface side. We experimentally indicated that the pressure fluctuation of the leading edge was the source of the periodicity noise.

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Noise due to turbulent flow past a trailing edge

Cited by 807 publications

References 19 publications

Prediction of Contra-Rotating Open Rotor broadband noise in isolated and installed configurations

Prediction of Contra-Rotating Open Rotor broadband noise in isolated and installed configurations

A second golden age of aeroacoustics?

Determination of Aerodynamic Sound Sources on Periodicity Noise Generated from a Micro Wind Turbine

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