Wall-Mounted Finite Airfoil-Noise Production and Prediction

Moreau, Danielle; Doolan, Con J.; Alexander, William N.; Meyers, Timothy W.; Devenport, William J.

doi:10.2514/1.j054493

Cited by 32 publications

(6 citation statements)

References 25 publications

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“…The tip vortex formation noise appears to have no influence in the frequency range of interest since the peak predicted tip vortex formation noise is at approximately 20 kHz (not shown). Recently Moreau et al 26 developed an empirical model based on wall-mounted finite airfoil measurements for predicting tip vortex formation noise. According to that model, the peak tip vortex formation noise is expected to occur around Strouhal number based on chord of 22.…”

Section: Resultsmentioning

confidence: 99%

“…This difference is due to the differences in flow around the airfoil on which the models are based. The Moreau et al 26 model is based on span varying flow conditions while the BPM model assumes uniform flow characteristics across the span. According to these flow characteristics, the model by Moreau et al 26 appears to be more suited for predicting tip vortex formation noise of rotating airfoils at 10 pitch angle.…”

Section: Resultsmentioning

confidence: 99%

“…The Moreau et al 26 model is based on span varying flow conditions while the BPM model assumes uniform flow characteristics across the span. According to these flow characteristics, the model by Moreau et al 26 appears to be more suited for predicting tip vortex formation noise of rotating airfoils at 10 pitch angle. However, the validity of either tip vortex noise prediction model cannot be confirmed due to the high frequency limitations of the microphone array used in this study.…”

Section: Resultsmentioning

confidence: 99%

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Experimental investigation of trailing edge noise from stationary and rotating airfoils

Zajamšek

Doolan

Moreau

et al. 2017

The Journal of the Acoustical Society of America

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Trailing edge noise from stationary and rotating NACA 0012 airfoils is characterised and compared with a noise prediction based on the semi-empirical Brooks, Pope, and Marcolini (BPM) model. The NACA 0012 is symmetrical airfoil with no camber and 12% thickness to chord length ratio. Acoustic measurements were conducted in an anechoic wind tunnel using a stationary NACA 0012 airfoil at 0° pitch angle. Airfoil self-noise emissions from rotating NACA 0012 airfoils mounted at 0° and 10° pitch angles on a rotor-rig are studied in an anechoic room. The measurements were carried out using microphone arrays for noise localisation and magnitude estimation using beamforming post-processing. Results show good agreement between peak radiating trailing edge noise emissions of stationary and rotating NACA 0012 airfoils in terms of the Strouhal number. Furthermore, it is shown that noise predictions based on the BPM model considering only two dimensional flow effects, are in good agreement with measurements for rotating airfoils, at these particular conditions.

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Section: Resultsmentioning

confidence: 99%

Section: Resultsmentioning

confidence: 99%

Section: Resultsmentioning

confidence: 99%

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Experimental investigation of trailing edge noise from stationary and rotating airfoils

Zajamšek

Doolan

Moreau

et al. 2017

The Journal of the Acoustical Society of America

Self Cite

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show abstract

“…Effective angle of attack as well as the Reynolds number is associated with Strouhal number st' and boundary layer height on the pressure side 𝛿 𝑃 . The empirical model can predict well the primary noise from a wall-mounted finite airfoil [25].…”

Section: Introductionmentioning

confidence: 96%

“…Without these, the generation of the airfoil whistle noise may not be understood and may inhibit an in-depth explanation of the measured results. Alternatively, analysis of dynamic cases such as oscillations of the trailing edge has gained interest recently [25]. It has also been proven that it has significant effects on the noise generated [26,27].…”

Section: Introductionmentioning

confidence: 99%

A Review on Generation and Mitigation of Airfoil Self-Induced Noise

Ibren

Andan

Asrar

et al. 2021

ARFMTS

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A review on passive acoustic control of airfoil self-noise by means of porous trailing edge is presented. Porous surfaces are defined using various terms such as porosity, permeability, resistivity, porosity constant, dimensionless permeability, flow control severity and tortuosity. The primary purpose of this review paper is to provide key findings regarding the sources and mitigation techniques of self-induced noise generated by airfoils. In addition, various parametric design concepts were presented, which are critically important for porous-airfoil design specifications. Most research focus on experimentation with some recent efforts on numerical simulations. Detail study on flow topology is required to fully understand the unsteady flow nature. In general, noise on the airfoil surface is linked to the vortex shedding, instabilities on the surface, as well as feedback mechanism. In addition, acoustic scattering can be minimized by reducing extent of the porous region from the trailing edge while increasing resistivity. Moreover, blowing might also be another means of reducing noise near the trailing edge. Ultimately, understanding the flow physics well provides a way to unveil the unknowns in self-induced airfoil noise generation, mitigation, and control.

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Wind Turbine Aerodynamic Noise Sources

Bertagnolio¹,

Fischer²

2021

Handbook of Wind Energy Aerodynamics

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Wall-Mounted Finite Airfoil-Noise Production and Prediction

Cited by 32 publications

References 25 publications

Experimental investigation of trailing edge noise from stationary and rotating airfoils

Experimental investigation of trailing edge noise from stationary and rotating airfoils

A Review on Generation and Mitigation of Airfoil Self-Induced Noise

Wind Turbine Aerodynamic Noise Sources

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