On the effects of anisotropic turbulence on leading edge noise

Gea-Aguilera, Fernando; Karve, Ravish; Gill, James; Zhang, Xin; Angland, David

doi:10.1016/j.jsv.2020.115895

Cited by 11 publications

(12 citation statements)

References 36 publications

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“…Non-uniform mean flows, whether upstream or near the airfoil, generally cause turbulence anisotropy. The effects of turbulence anisotropy on leading edge noise have been reviewed and studied recently by Gea-Aguilera et al 130,131 and by Zhong and Zhang. 117 The effects of angle of attack 116 and camber have been found to be small for isotropic turbulence.…”

Section: Broadband Noisementioning

confidence: 99%

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Challenges and opportunities for low noise electric aircraft

Greenwood

Brentner

Rau

et al. 2022

International Journal of Aeroacoustics

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A new class of electric aircraft is being developed to transport people and goods as a part of the urban and regional transportation infrastructure. To gain public acceptance of these operations, these aircraft need to be much quieter than conventional airplanes and helicopters. This article seeks to review and summarize the aeroacoustic research relevant to this new category of aircraft. First, a brief review of the history of electric aircraft is provided, with an emphasis on how these aircraft differ from conventional aircraft. Next, the physics of rotor noise generation are reviewed, and the noise sources most likely to be of concern for electric aircraft are highlighted. These are divided into deterministic and nondeterministic sources of noise. Deterministic noise is expected to be dominated by the unsteady loading noise caused by the aerodynamic interactions between components. Nondeterministic noise will be generated by the interaction of the rotor or propeller blades with turbulence from ingested wakes, the atmosphere, and self-generated in the boundary layer. The literature for these noise sources is reviewed with a focus on applicability to electric aircraft. Challenges faced by the aeroacoustician in understanding the noise generation of electric aircraft are then identified, as well as the new opportunities for the prediction and reduction of electric aircraft noise that may be enabled by advances in computational aeroacoustics, flight simulation, and autonomy.

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Section: Broadband Noisementioning

confidence: 99%

“…117 The effects of angle of attack 116 and camber have been found to be small for isotropic turbulence. 111,131 However, as reviewed by Roger and Moreau, 111 it is unclear if this conclusion also holds for anistropic turbulence. 112,130,132…”

Section: Broadband Noisementioning

confidence: 99%

Challenges and opportunities for low noise electric aircraft

Greenwood

Brentner

Rau

et al. 2022

International Journal of Aeroacoustics

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“…The buffer-zone method is used to minimise the spurious reflections. 39 It has been employed for various aeroacoustic problems including the leading edge noise 11,[14][15][16][17][18][19][20] that is studied in this work. The key measure of IBM is to introduce additional equivalent terms to the original governing equations on account of the corresponding boundary conditions.…”

Section: Computational Aeroacoustics Solvermentioning

confidence: 99%

“…[2][3][4][5][6][7][8][9][10] Another approach is based on the numerical simulations with the developments in computational aeroacoustics (CAA), which is efficient in investigating the impact of influential parameters and revealing the underneath mechanisms. 3,[11][12][13][14][15][16][17][18][19] Another example of the practical geometrical impact is due to the periodically arranged cascade blades. 15,[20][21][22] For these studies, the synthetic turbulence method was often employed to reproduce the divergence-free turbulent fluctuations in the computational domain.…”

Section: Introductionmentioning

confidence: 99%

Computational aeroacoustics of aerofoil leading edge noise using the volume penalization-based immersed boundary methods

Ying

Fattah

Cantos

et al. 2022

International Journal of Aeroacoustics

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Broadband noise due to the turbulence-aerofoil interaction, which is also called the leading edge noise, is one of the major noise sources of aircraft (including the engine). To study the noise properties numerically is a popular approach with the increasing power of computers. Conventional approaches of using body-fitted grids at the boundaries would be convoluted due to the complex geometries, which can constrain the efficiency of parametric studies. A promising approach to tackle this issue is to use the immersed boundary method (IBM). Among various IBM variants, the volume penalization (VP) approach employs a masking function to identify the immersed solid boundary, and continuous forcing terms are added to the original flow governing equations to account for the boundary conditions. It is, therefore, efficient and easy to implement into the existing computational aeroacoustics solvers. In this work, the VP-based IBM is used to simulate the leading edge noise by combining with the advanced synthetic turbulence method. The simulations are conducted for both the isolated aerofoils and cascade, and the results are compared with the well-validated body-fitted grid solutions. The viscosity effect is also highlighted by comparing the results obtained by solving both Euler and Navier–Stokes equations.

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“…The generation of a fully 3D turbulence structure represents still a challenging issue. Several methods have emerged to tackle this issue such as Synthetic Eddy Method (SEM) [6,7], extended to anisotropic flows and serrated airfoils [8,9], and Random Particle Mesh (RPM) methodology [10] with recent developments to generate 3D turbulence fields [11,12]. In this paper, the focus is put on the synthetic turbulence modeling with a particular interest on the development and implementation of a fully three-dimensional vector field (with the complete 3-wavenumbers spectrum and 3-velocity components).…”

Section: Introductionmentioning

confidence: 99%

3D CAA methodology using synthetic turbulence to assess turbulence-cascade interaction noise emission and reduction from serrated airfoils

Buszyk¹,

Polacsek²,

Barrier³

et al. 2021

Aiaa Aviation 2021 Forum

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HAL is a multi-disciplinary open access archive for the deposit and dissemination of scientific research documents, whether they are published or not. The documents may come from teaching and research institutions in France or abroad, or from public or private research centers. L'archive ouverte pluridisciplinaire HAL, est destinée au dépôt et à la diffusion de documents scientifiques de niveau recherche, publiés ou non, émanant des établissements d'enseignement et de recherche français ou étrangers, des laboratoires publics ou privés.

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On the effects of anisotropic turbulence on leading edge noise

Cited by 11 publications

References 36 publications

Challenges and opportunities for low noise electric aircraft

Challenges and opportunities for low noise electric aircraft

Computational aeroacoustics of aerofoil leading edge noise using the volume penalization-based immersed boundary methods

3D CAA methodology using synthetic turbulence to assess turbulence-cascade interaction noise emission and reduction from serrated airfoils

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