Trailing-edge noise prediction using large-eddy simulation and acoustic analogy

Manoha, Eric; Troff, B.; Sagaut, Pierre

doi:10.2514/3.14447

Cited by 15 publications

(20 citation statements)

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“…13, the single-airfoil formulation (5) is first applied to calculate the radiated sound from one azimuthal location with no account of the relative motion with respect to the observer, but with the actual flow parameters relative to the segment according to the local velocity triangle. It must be noted that formulation (5) has been preferred to the more general one for arbitrary aspect ratio, involving a sine cardinal function. Indeed, it has been recently observed that using the general formulation, the noise predicted for a single airfoil can be slightly different from the cumulated noise as calculated by the sum of the contributions from a given number of sub-parts of the same airfoil.…”

Section: Trailing-edge Noise Model For a Rotating Bladementioning

confidence: 99%

“…On airfoils, it can be deduced either from dedicated experiments, using for instance remote microphone probes, [12][13][14] or from detailed numerical simulations such as Large-Eddy Simulations (LES). 4,5,[15][16][17] Dealing with a rotating fan blade, LES is still too computationally intensive to model the acoustic sources accurately. One has then to resort to specific detailed measurements to characterize the noise sources.…”

Section: Experimental Set-upmentioning

confidence: 99%

“…The detailed description of the flow around the airfoil trailing edge of an airfoil has provided the strength of the acoustic sources. 4,5 Given the source distribution, various numerical or analytical approaches to evaluate the trailing-edge noise have been developed. Casper & Farassat 6 proposed a timedomain formulation considering a flat plate in a non-uniform flow, based on the fluctuating surface pressure distribution.…”

Section: Introductionmentioning

confidence: 99%

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Rotating Blade Trailing-Edge Noise: Experimental Validation of Analytical Model

2010

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The paper is dealing with the experimental validation of an analytical trailing-edge noise model dedicated to low-speed fans operating in free field.The model is intrinsically related to the aerodynamics of the blades and should lead to a useful fast-running tool to be included in a blade design process in an industrial context. The investigations are made on a two- = distance between the fan axis and the mid-span network r 2 = distance between the fan axis and the tip network R = radial distance R 0 = distance between observer position and fan center R A = position vector of the middle of the trailing-edge segment in the moving reference frame R e = Reynolds number= corrected distance for convection effects S pp = acoustic pressure power spectral density S Ψ pp = acoustic pressure power spectral density due to one blade segment U = tangential velocity U c = convection velocity (x 1 , x 2 , x 3 ) = moving reference frame x = observer position in the moving reference frame (X, Y, Z) = fixed reference frame X = observer position in the fixed reference frame α g = airfoil angle of attack= cross spectral phase between signals i and j Φ pp = wall-pressure power spectral densitỹ Φ pp = normalized wall-pressure power spectral density Θ = azimuthal observer angle ρ = fluid density τ w = wall shear stress ω = radian frequency ω e = emission radian frequency Ω = fan angular velocity ξ = streamwise distance

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Section: Trailing-edge Noise Model For a Rotating Bladementioning

confidence: 99%

Section: Experimental Set-upmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Rotating Blade Trailing-Edge Noise: Experimental Validation of Analytical Model

2010

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“…Mach numbers between 0.2 and 0.5 were considered. It was found that the sound intensity scaled approximately as M 4 downstream of the airfoil and that taking into account non-linearities could increase or reduce the sound pressure levels depending on the sign of the initial vortex disturbance. Singer et al [2] simulated the acoustic scattering from vortices convecting past the trailing edge of a thin symmetrical airfoil, also at zero degrees angle of attack with Mach number varying between 0.2 and 0.4.…”

Section: Introductionmentioning

confidence: 99%

“…Other recent CFD studies include the use of Large Eddy Simulation (LES) for the prediction of TE noise. Manoha et al [3] computed the noise radiated from a 3D lifting airfoil using a compressible threedimensional LES [4]. A NACA0012 airfoil placed at 5°a ngle of attack and a flow Mach number of 0.205 was modeled.…”

Section: Introductionmentioning

confidence: 99%

Effects of Angle of Attack and Velocity on Trailing Edge Noise

Hutcheson

Brooks

2004

42nd AIAA Aerospace Sciences Meeting and Exhibit

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Trailing edge (TE) noise measurements for a NACA 63-215 airfoil model are presented, providing benchmark experimental data for a cambered airfoil. The effects of flow Mach number and angle of attack of the airfoil model with different TE bluntnesses are shown. Far-field noise spectra and directivity are obtained using a directional microphone array. Standard and diagonal removal beamforming techniques are evaluated employing tailored weighting functions for quantitatively accounting for the distributed line character of TE noise. Diagonal removal processing is used for the primary database as it successfully removes noise contaminates. Some TE noise predictions are reported to help interpret the data, with respect to flow speed, angle of attack, and TE bluntness on spectral shape and peak levels. Important findings include the validation of a TE noise directivity function for different airfoil angles of attack and the demonstration of the importance of the directivity function's convective amplification terms.

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Zonal multi‐domain RANS/LES simulations of turbulent flows

Quemere

Sagaut

2002

Numerical Methods in Fluids

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A new zonal multi-domain Reynolds averaged numerical simulation=large-Eddy simulation (RANS=LES) method is presented and assessed. The main occurring problem is the coupling at the domain interfaces between a 1D or 2D, ensemble averaged solution computed with the RANS approach with the 3D, ÿltered, unsteady solution obtained using the LES approach. Both low-and high-normal velocity interface cases are considered, resulting in a fully general approach. A coupling procedure well suited for cell-centred ÿnite volume numerical method is proposed. Numerical tests are carried out for the plane channel and the plane plate with a blunt trailing-edge conÿgurations.

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Trailing-edge noise prediction using large-eddy simulation and acoustic analogy

Cited by 15 publications

References 0 publications

Rotating Blade Trailing-Edge Noise: Experimental Validation of Analytical Model

Rotating Blade Trailing-Edge Noise: Experimental Validation of Analytical Model

Effects of Angle of Attack and Velocity on Trailing Edge Noise

Zonal multi‐domain RANS/LES simulations of turbulent flows

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