Noise Radiated by a High-Reynolds-number 3-D Airfoil

Marsden, Olivier; Bogey, Christophe; Bailly, Christophe

doi:10.2514/6.2005-2817

Cited by 8 publications

(5 citation statements)

References 30 publications

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“…This LES approach was recently successfully applied to isotropic turbulence, channel flows, jets and flows around an airfoil, by Visbal et al, 37,38 Mathew et al, 39 and the present authors. 32,40 The explicit selective filtering used here is also very similar 41 to the relaxation term introduced by Stolz et al 42 in their approximate deconvolution model.…”

Section: A Governing Equationsmentioning

confidence: 96%

“…Further it is not strictly necessary for stability and it is not used in the latest LES performed in our group. 40,43 The value of d and the frequency of filtering are arbitrary, but they are expected to have a negligible influence on the results due to the selectivity of the filters. It was also shown previously that applying the filtering every second or third time step provides very similar features for the highReynolds-number jet LEShre presented in the next sections.…”

Section: B Numerical Proceduresmentioning

confidence: 99%

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Large eddy simulations of transitional round jets: Influence of the Reynolds number on flow development and energy dissipation

2006

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Transitional round jets at Mach number M=0.9, with identical initial conditions except for the diameter, yielding Reynolds numbers over the range 1.7×103⩽ReD⩽4×105, are computed by large eddy simulation (LES) using explicit selective/high-order filtering. The effects of the Reynolds number on the jet flows are first presented. As the Reynolds number decreases, the jets develop more slowly upstream from the end of the potential core, but more rapidly downstream. At lower Reynolds numbers, the decay of the centerline velocity and the jet spreading are indeed faster, and the turbulence intensities are higher after the potential core, in agreement with data of the literature. The integral length scales are also significantly larger. The results suggest moreover that the jet self-similar region is reached at shorter axial distances at lower Reynolds numbers. The influence of the Reynolds number on the energy-dissipation mechanisms involved in the LES, namely molecular viscosity and explicit filtering, is secondly investigated. At high Reynolds number, energy dissipation is mainly ensured by the explicit filtering, through the smaller scales discretized. As the Reynolds number decreases, the contribution of molecular viscosity increases and becomes predominant. Molecular viscosity is also shown to affect a large range of turbulent scales with a dissipation peak observed around the Taylor length scale.

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Section: A Governing Equationsmentioning

confidence: 96%

Section: B Numerical Proceduresmentioning

confidence: 99%

Large eddy simulations of transitional round jets: Influence of the Reynolds number on flow development and energy dissipation

2006

Self Cite

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“…They are designed to allow the accurate resolution of waves with at least five points per wavelength. Note that these schemes have been recently used for the direct computation of noise radiated by flows around nonCartesian bodies [17,18].…”

Section: Introductionmentioning

confidence: 99%

High-order, low dispersive and low dissipative explicit schemes for multiple-scale and boundary problems

Berland

Bogey

Marsden

et al. 2007

Journal of Computational Physics

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224

189

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“…Fleig and Lida et al [34] studied the tip vortex noise of rotating wind turbine blades. Marsden et al [35] used LES to study and compare the difference in surface boundary layer transition of the flow over airfoils in two and three dimensions. Results show that the method can accurately predict the position of boundary layer transition, as well as the aerodynamic noise.…”

Section: Introductionmentioning

confidence: 99%

Effect of Tailing-Edge Thickness on Aerodynamic Noise for Wind Turbine Airfoil

Yang

et al. 2019

Energies

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The influence of wind turbine airfoil trailing edge thickness on aerodynamics and aerodynamic noise characteristics was studied using the computational fluid dynamics (CFD)/ Ffowcs Williams–Hawkings (FW–H) method in the present work. First, the airfoil of a DU97-W-300-flatback airfoil was chosen as the research object, and numerical method validation was performed. Three kinds of turbulence calculation methods (unsteady Reynolds average Navier-Stokes (URANS), detached eddy simulation (DES), and large eddy simulation (LES)) were investigated in detail, and three sets of grid scales were used to study the impact of the airfoil on the aerodynamic noise. Secondly, the airfoil trailing edge thickness was changed, and the impact of trailing edge thickness on aerodynamics and aerodynamic noise was investigated. Results show that three kinds of turbulence calculation methods yield the same sound pressure frequency, and the magnitude of the sound pressure level (SPL) corresponding to the mean frequency is almost the same. The calculation of the SPL of the peak value and the experimental results can match well with each other, but the calculated core frequency is slightly lower than the experimental frequency. The results of URANS and DES are closer to each other with a changing trend of SPL, and the consequences of the DES calculation are closer to the experimental results. From the comparison of two airfoils, the blunt trailing edge (BTE) airfoil has higher lift and drag coefficients than the original airfoil. The basic frequency of lift coefficients of the BTE airfoil is less than that of the original airfoil. It is demonstrated that the trailing vortex shedding frequency of the original airfoil is higher than that of the BTE airfoil. At a small angle of attack (AOA), the distribution of SPL for the original airfoil exhibits low frequency characteristics, while, at high AOA, the wide frequency characteristic is presented. For the BTE airfoil, the distribution of SPL exhibits low frequency characteristics for the range of the AOA. The maximum AOA of SPL is 4° and the minimum AOA of SPL is 15°, while, for the original airfoil, the maximum AOA of SPL is 19°, and the minimum AOA is 8°. For most AOAs, the SPL of the BTE airfoil is larger than that of the original airfoil.

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Noise Radiated by a High-Reynolds-number 3-D Airfoil

Cited by 8 publications

References 30 publications

Large eddy simulations of transitional round jets: Influence of the Reynolds number on flow development and energy dissipation

Large eddy simulations of transitional round jets: Influence of the Reynolds number on flow development and energy dissipation

High-order, low dispersive and low dissipative explicit schemes for multiple-scale and boundary problems

Effect of Tailing-Edge Thickness on Aerodynamic Noise for Wind Turbine Airfoil

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