Effect of Airfoil Aerodynamic Loading on Trailing Edge Noise Sources

Moreau, Stéphane; Roger, Michel

doi:10.2514/1.5578

Cited by 122 publications

(92 citation statements)

References 15 publications

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“…Aerodynamic and acoustic data are collected to study trailing-edge noise. The experimental setup has already been described by Moreau & Roger [34,39]. The mock-up has a chord length of 13.6 cm and a span of 30 cm.…”

Section: V2 Airfoilmentioning

confidence: 99%

Wall-Pressure Spectral Model Including the Adverse Pressure Gradient Effects

2012

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An empirical model to predict the wall-pressure fluctuations spectra beneath adverse pressure gradient flows is presented. It is based on Goody's model which already incorporates the effect of Reynolds number but is limited to zero-pressure gradient flows. The extension relies on 6 test-cases from 5 experimental or numerical studies covering a large range of Reynolds number, 5.6 × 10 2 < R θ < 1.72 × 10 4 , in both inter-

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Section: V2 Airfoilmentioning

confidence: 99%

Wall-Pressure Spectral Model Including the Adverse Pressure Gradient Effects

2012

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“…The statistics of the aerodynamic pressure induced in the trailing-edge region by the turbulent boundary-layer is most often required for such models. 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.…”

Section: Experimental Set-upmentioning

confidence: 99%

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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“…This profile reduces drag and has been used for turboengine compressor blades, automotive engine cooling fan systems, and heat and ventilation air-conditioning systems. The aerodynamic and acoustic characteristics of this profile have been investigated both numerically and experimentally [8][9][10][11][12] especially at moderate and high angles of attack. In the present study, noise generated by this profile at low angle of attack is experimentally studied.…”

Section: Introductionmentioning

confidence: 99%

Tonal noise of a controlled-diffusion airfoil at low angle of attack and Reynolds number

Padois¹,

Laffay²,

Idier³

et al. 2016

The Journal of the Acoustical Society of America

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The acoustic signature of a controlled-diffusion airfoil immersed in a flow is experimentally characterized. Acoustic measurements have been carried out in an anechoic open-jet-wind-tunnel for low Reynolds numbers (from 5 × 104 to 4.3 × 105) and several angles of attack. As with the NACA0012, the acoustic spectrum is dominated by discrete tones. These tonal behaviors are divided into three different regimes. The first one is characterized by a dominant primary tone which is steady over time, surrounded by secondary peaks. The second consists of two unsteady primary tones associated with secondary peaks and the third consists of a hump dominated by several small peaks. A wavelet study allows one to identify an amplitude modulation of the acoustic signal mainly for the unsteady tonal regime. This amplitude modulation is equal to the frequency interval between two successive tones. Finally, a bispectral analysis explains the presence of tones at higher frequencies.

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Effect of Airfoil Aerodynamic Loading on Trailing Edge Noise Sources

Cited by 122 publications

References 15 publications

Wall-Pressure Spectral Model Including the Adverse Pressure Gradient Effects

Wall-Pressure Spectral Model Including the Adverse Pressure Gradient Effects

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

Tonal noise of a controlled-diffusion airfoil at low angle of attack and Reynolds number

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