Noise Radiation from Single and Multiple Rod Configurations

Hutcheson, Florence V.; Brooks, Thomas F.

doi:10.1260/1475-472x.11.3-4.291

Cited by 69 publications

(72 citation statements)

References 31 publications

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“…Good agreement is found, with maximum differences of 2 dB between the measured and theoretical values. These results agree with those obtained by Porteous et al [16] and Hutcheson and Brooks [17]. For some of the radiation angles the dispersion in the results is large, around +/-3 dB.…”

Section: Directivitysupporting

confidence: 92%

“…Moreau and Doolan [15] also studied the effect of the aspect ratio of a wall-mounted circular cylinder with a free end on the noise radiation (Re from 1.0 × 10 4 to 1.4 × 10 4 ), the results being extended to the assessment of the directivity by Porteous et al [16]. Hutcheson and Brooks [17] studied the effect of incoming turbulence on the noise radiated by circular and square cylinders for Reynolds numbers in the range 3.8 × 10 3 to 1.0 × 10 5 using grids of different sizes to generate the turbulence. They assessed the effect of the cylinder surface roughness by placing grit with small particle size on the cylinder surface.…”

Section: Introductionmentioning

confidence: 99%

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Experimental study of the aerodynamic noise radiated by cylinders with different cross-sections and yaw angles

Iglesias

Thompson

Smith

2016

Journal of Sound and Vibration

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Vortex shedding from cylinders has been extensively studied due to its occurrence in many engineering fields. Many experimental studies reported in the literature focus on the aerodynamics of the vortex shedding process but the literature about the radiated noise is more scarce. The aim of the work presented here is to extend the available noise data. Aero-acoustic wind tunnel tests were carried out using cylinders with different cross-sections: circular, square, rectangular and elliptical. Flow speeds between 20 and 50 m/s were used, corresponding to Reynolds numbers in the range from 1.6 × 10 4 to 1.2 × 10 5 . The dependence of the noise on the yaw angle, flow speed, cross-sectional shape, angle of attack and radiation angle (directivity) is assessed. The results obtained are compared, where possible, with those found in the literature for similar cases. It is intended that the results can be used for the validation and calibration of numerical and empirical aerodynamic noise prediction models.

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Section: Directivitysupporting

confidence: 92%

Section: Introductionmentioning

confidence: 99%

Experimental study of the aerodynamic noise radiated by cylinders with different cross-sections and yaw angles

Iglesias

Thompson

Smith

2016

Journal of Sound and Vibration

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“…In nearly all cases, the sound powers scale with the sixth power of the flow velocity. This velocity dependence is usually associated with vortex shedding noises from bluff bodies [23] and an airfoil with a blunt trailing edge [17]. For the S0 baseline case, we also have observed a velocity scaling of…”

Section: B Broadband Noise Reduction By Trailing Edge Serrationssupporting

confidence: 51%

Self-Noise Produced by an Airfoil with Nonflat Plate Trailing-Edge Serrations

et al. 2013

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This paper represents the results of an experimental study aimed at reducing the airfoil self-noise by the trailing edge serration of four different sawtooth geometries (defined in the serration angle and length). These serrations have a common feature: all of the sawtooth patterns are cut directly into the trailing edge of a realistic airfoil. This configuration offers better structural strength and integrity. For the sawtooth trailing edges investigated here, the radiation of the extraneous vortex shedding noise in a narrowband frequency due to the partial bluntness at the serration roots is unavoidable. However, this narrowband component tends to be less significant provided that the serration angle is large and the serration length is moderate. Sound power was measured, and some of the sawtooth geometries have been shown to afford significant boundarylayer instability tonal noise and moderate turbulent broadband noise reductions across a fairly large velocity range. This paper demonstrates that a nonflat plate serrated trailing edge can also be effective in the selfnoise reduction. Some experimental results are also presented in order to explain the self-noise mechanisms. Chong et al. (corresponding author3

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“…Such a simplified configuration constitutes an ideal test case for investigating the physics of aerodynamic noise associated with component interaction as well as validating high-fidelity numerical prediction tools for similar sources of noise in actual aircraft undercarriage systems. To this end, extensive experimental data has been [8][9][10][11] and compared to the results of 3-D, unsteady CFD computations 12,13 . Despite the favorable comparison between the measured and computed spectra, a legitimate concern existed about some of the obvious differences occurring between the installed TC configuration that had been tested and the simplified configuration that was computed.…”

Section: A Backgroundmentioning

confidence: 99%