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Academic literature on the topic 'Wind tunnel noise'

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Published: 10 December 2022
Last updated: 29 January 2023

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Journal articles on the topic "Wind tunnel noise"

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IIDA, Akiyoshi. "Low Noise Wind Tunnel." Journal of the Society of Mechanical Engineers 108, no. 1042 (2005): 726–27. http://dx.doi.org/10.1299/jsmemag.108.1042_726.

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MAEDA, Tatsuo, and Yoshihiko KONDO. "RTRI's Large-scale Low-noise Wind Tunnel and Wind Tunnel Tests." Quarterly Report of RTRI 42, no. 2 (2001): 65–70. http://dx.doi.org/10.2219/rtriqr.42.65.

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Baumeister, K. J. "Reverberation Effects on Directionality and Response of Stationary Monopole and Dipole Sources in a Wind Tunnel." Journal of Vibration and Acoustics 108, no. 1 (January 1, 1986): 82–90. http://dx.doi.org/10.1115/1.3269307.

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Analytical solutions for the three-dimensional inhomogeneous wave equation with flow in a hardwall rectangular wind tunnel and in the free field are presented for a stationary monopole noise source. Dipole noise sources are calculated by combining two monopoles 180 deg out of phase. Numerical calculations for the modal content, spectral response and directivity for both monopole and dipole sources are presented. In addition, the effect of tunnel alterations, such as the addition of a mounting plate, on the tunnels reverberant response are considered. In the frequency range of practical importance for the turboprop response, important features of the free field directivity can be approximated in a hardwall wind tunnel with flow if the major lobe of the noise source is not directed upstream. However, for an omnidirectional source, such as a monopole, the hardwall wind tunnel and free field response will not be comparable.
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Migliore, Paul, and Stefan Oerlemans. "Wind Tunnel Aeroacoustic Tests of Six Airfoils for Use on Small Wind Turbines*." Journal of Solar Energy Engineering 126, no. 4 (November 1, 2004): 974–85. http://dx.doi.org/10.1115/1.1790535.

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Aeroacoustic tests of seven airfoils were performed in an open jet anechoic wind tunnel. Six of the airfoils are candidates for use on small wind turbines operating at low Reynolds numbers. One airfoil was tested for comparison to benchmark data. Tests were conducted with and without boundary layer tripping. In some cases, a turbulence grid was placed upstream in the test section to investigate inflow turbulence noise. An array of 48 microphones was used to locate noise sources and separate airfoil noise from extraneous tunnel noise. Trailing-edge noise was dominant for all airfoils in clean tunnel flow. With the boundary layer untripped, several airfoils exhibited pure tones that disappeared after proper tripping was applied. In the presence of inflow turbulence, leading-edge noise was dominant for all airfoils.
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Chu, Yijing, Sipei Zhao, Longbiao He, and Feng Niu. "Wind noise suppression in filtered-x least mean squares-based active noise control systems." Journal of the Acoustical Society of America 152, no. 6 (December 2022): 3340–45. http://dx.doi.org/10.1121/10.0016443.

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Wind noise is notorious for its detrimental impacts on audio devices. This letter evaluates the influence of wind noise on the active noise control performance of headphones in a wind tunnel, and the noise reduction is found to decrease with wind speeds. To improve the performance of noise control systems in windy environments, the filtered-x least mean squares algorithm is modified based on the total least squares technique, taking the characteristics of wind noise into account. Computer simulations with real-recorded data demonstrate that the proposed algorithm could improve the noise reduction by approximately 3 dB in windy conditions.
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Li, Zhengnong, and Jianan Li. "Numerical Simulation Study of Aerodynamic Noise in High-Rise Buildings." Applied Sciences 12, no. 19 (September 21, 2022): 9446. http://dx.doi.org/10.3390/app12199446.

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In order to study the aerodynamic noise on the surfaces of high-rise buildings under the action of strong winds, this paper numerically simulated the sound pressure field on the surface of a high-rise building using the large-eddy simulation method combined with the acoustic analog method of FW-H (Ffowcs Williams–Hawkings) equation and obtained the intensity radiation distribution of sound pressure on the surface of the building to further identify the area with the maximum sound pressure intensity of the noise radiation and thus achieve the purpose of locating noise source. The accuracy of the numerical simulation results for aerodynamic noise obtained in this paper was then verified by comparing with the acoustic wind tunnel experimental results. The locations of noise source obtained by numerical simulation and acoustic wind tunnel experiment were in good agreement. The sound pressure intensity pulsation time course was measured by the acoustic wind tunnel experiment, and the noise sound pressure level spectrum of each part of the building surface was obtained by fast Fourier transform (FFT). Furthermore, the spectral characteristics of the noise sound pressure level were analyzed. The results of the sound pressure level spectrum of aerodynamic noise obtained from the numerical simulation were compared with the acoustic wind tunnel experimental results, which were found to be very similar. The analysis of the sound pressure level spectrum of aerodynamic noise on the building surface reveals that the numerical simulation results in the middle- and high-frequency bands of the spectrum are in good agreement with the acoustic wind tunnel experimental results, but there is a difference between those in the low-frequency bands and the acoustic wind tunnel experimental results. The microphone array used to locate the noise source in the acoustic wind tunnel was found to suffer non-eliminable measurement errors, which might be a potential reason for a reasonably slight difference between the experimental and numerical simulation results. The background noise in the low-frequency band of the acoustic wind tunnel sound pressure level spectrum was relatively large, while there was basically no background noise in the numerical simulation. This paper shows that the numerical simulation method combined with large-eddy simulation and acoustic analogy (FW-H) can calculate the aerodynamic noise intensity at various points on the surfaces of high-rise buildings and reasonably predict the location of sound source. In addition, the numerical simulation results are similar to the acoustic wind tunnel experimental results in most frequency bands.
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Li, Hanqin, Bin Fang, and Yongming Zhang. "Research on an Anechoic Wind Tunnel in the Design Phase by Numerical Simulation." Journal of Physics: Conference Series 2173, no. 1 (January 1, 2022): 012006. http://dx.doi.org/10.1088/1742-6596/2173/1/012006.

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Abstract As an important facility for acoustic measurement and research in air medium, anechoic wind tunnel requires high acoustic performance. In this paper, the flow field and acoustic characteristics of anechoic wind tunnel were studied by modeling and simulation. The velocity and pressure distribution of the whole flow field in the wind tunnel are obtained by simulation calculation, and the noise source distribution in the anechoic wind tunnel is studied by the broadband noise source method, which provides a reference for the design, construction and optimization of the anechoic wind tunnel.
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Chen, Jiming, Shenghao Wu, Zhenhua Chen, Jinlei Lyu, and Haitao Pei. "Experimental Research on Noise Reduction for Continuous Transonic Wind Tunnel Loop." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 38, no. 4 (August 2020): 855–61. http://dx.doi.org/10.1051/jnwpu/20203840855.

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The noise level of wind tunnel test section is respected as one of the most important performance specifications to represent the flow field quality, especially for large scale wind tunnel. According to the acoustic experimental research conducted in the 0.6 m continuous transonic wind tunnel of CARDC, main noise sources in the tunnel loop included the compressor, the high-speed diffuser and the test section. To reduce the noise in the test section, it is necessary to prevent the test section from the compressor noise propagated both forward and backward. In 0.6 m wind tunnel loop, acoustic treatments were installed on both the compressor rear cone and the fourth corner to prevent the noise emitted from the compressor from propagating forward. The vanes in the forth corner were filled with glass fibers and covered with perforated panels. And the compressor rear cone was covered with three layers of micro-perforated panels. With acoustic treatment in the tunnel loop and the second throat throttling, the fluctuation pressure coefficient (ΔCp) is lower than 0.8%, which is close to the international advanced level.
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Nachaiyaphum, Kwanjai, and Chonlatee Photong. "An electric power generation improvement for small Savonius wind turbines under low-speed wind." Indonesian Journal of Electrical Engineering and Computer Science 29, no. 2 (February 1, 2023): 618. http://dx.doi.org/10.11591/ijeecs.v29.i2.pp618-625.

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<p>Savonius wind turbines have advantages of self-rotating at low speed wind, high starting torque, and less noise generation. However, they have low electric power generation capacity. This paper presents electric power generation improvement for small Savonius wind turbines when operating at low-speed wind of 1-6 m/s by using optimal Bach-type blades, twist blades and a wind tunnel. The turbine prototypes with the optimum diameter and height of 32 cm were developed with 3 different blade types: conventional semicircular blades, Bach-type blades and twisted 15° blades and a wind tunnel. The experimental results showed that the Savonius wind turbine with Bach-type generated highest electric voltage, which was 19.3% and 7.6% higher compared to conventional blades and twisted 15° blades. The additional wind tunnel could improve electric power generation efficiency by approximately 21.4% compared to the turbines without the tunnels.</p>
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IDO, Atsushi. "RTRI's Large-Scale Low-Noise Wind Tunnel." Journal of the Visualization Society of Japan 32, no. 124 (2012): 26–31. http://dx.doi.org/10.3154/jvs.32.124_26.

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Dissertations / Theses on the topic "Wind tunnel noise"

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Stoker, Robert W. "A method to separate wind-tunnel background noise and wind noise from interior measurements." Diss., Georgia Institute of Technology, 1996. http://hdl.handle.net/1853/12032.

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Grant, Justin Alexander. "Far-field noise from a rotor in a wind tunnel." Thesis, Florida Atlantic University, 2016. http://pqdtopen.proquest.com/#viewpdf?dispub=10154927.

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This project is intended to demonstrate the current state of knowledge in the prediction of the tonal and broadband noise radiation from a Sevik rotor. The rotor measurements were made at the Virginia Tech Stability Wind Tunnel. Details of the rotor noise and flow measurements were presented by Wisda et al(2014) and Murray et al(2015) respectively. This study presents predictions based on an approach detailed by Glegg et al(2015) for the broadband noise generated by a rotor in an inhomogeneous flow, and compares them to measured noise radiated from the rotor at prescribed observer locations. Discrepancies between the measurements and predictions led to comprehensive study of the flow in the wind tunnel and the discovery of a vortex upstream of the rotor at low advance ratios. The study presents results of RANS simulations. The static pressure and velocity profile in the domain near the rotor’s tip gap region were compared to measurements obtained from a pressure port array and a PIV visualization of the rotor in the wind tunnel

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Griffith, Dwaine O. "Turbulence measurements and noise generation in a transonic cryogenic wind tunnel." Thesis, Virginia Tech, 1989. http://hdl.handle.net/10919/45979.

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A high-frequency combination probe was used to measure dynamic flow quality in the test section of the NASA Langley 0.3-m Transonic Cryogenic Tunnel. The probe measures fluctuating stagnation (total) temperature and pressure, static pressure, and flow angles in two orthogonal planes. Simultaneous unsteady temperature and pressure measurements were also made in the settling chamber of the tunnel. The data show that the stagnation temperature fluctuations remain constant, and the stagnation pressure fluctuations increase by a factor of two, as the flow accelerates from the settling chamber to the test section. In the test section, the maximum rms value of the normalized fluctuating velocity is 0.7 percent. Correlation coefficients l failed to show vortlcity, entropy, or sound as the dominant mode of turbulence in the tunnel.

At certain tunnel operating conditions, periodic disturbances are seen in the data taken in the test section. A possible cause for the disturbances is found to be acoustic coupling of the test section and plenum chamber via the perforated side walls in the tunnel. The experimental data agree well with the acoustic coupling theory.


Master of Science
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Owens, David Elliot. "Wall Features of Wing-Body Junctions: Towards Noise Reduction." Thesis, Virginia Tech, 2013. http://hdl.handle.net/10919/23717.

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Much research and experiments have gone into studying idealized wing-body junction flows and their impact on horseshoe vortex and wake formation.  The vortices have been found to generate regions of high surface pressure fluctuations and turbulence that are detrimental to structural components and acoustics.  With the focus in the military and commercial industry on reducing the acoustical impact of aircraft and their engines, very little research has been done to examine the potential impact wing-body junctions may have on acoustics, especially for high lifting bodies such as propellers.  Two similar tests were conducted in the Virginia Tech Open Jet Wind Tunnel where boundary layer measurements, oil flow visualizations, acoustic linear array and surface pressure fluctuation measurements of a baseline Rood airfoil model and two novel junction fairing designs were all taken.  Boundary layer measurements were taken at four locations along the front half of the flat plate and the profiles were shown to be all turbulent despite the low Reynolds number of the flow, (test 1: Re_"<1400, test 2: Re_"<550).  Oil flow visualizations were taken and compared to those of previous researchers and the location of separation and line of low shear along with the maximum width of the wake and width of wake at the trailing edge all scaled relatively well with the Momentum Deficit Factor, defined for wing-body junction flows [Fleming, J. L., Simpson, R. L., Cowling, J. E. & Devenport, W. J., 1993. An Experimental Study of a Turbulent Wing-Body Junction and Wake Flow. Experiments in Fluids, Volume 14, pp. 366-378. ].  A linear microphone array was used to estimate the directivity of the facility acoustic background noise to be used to improve background subtraction methods for surface pressure fluctuation measurements.  Surface pressure fluctuation spectra were taken ahead of the leading edge of the plate and along the surface of the models.  These showed that the fairings reduced pressure fluctuations along the plate upstream of the leading edge, with fairing 1 reducing them to clean tunnel flow levels.  On the surface of the models, the fairings tended to reduce low frequency (<1000Hz) pressure fluctuation peaks when compared to the baseline model and increase the pressure fluctuations in the high frequency range.  Simple scaling arguments indicate that this spectral change may be more beneficial than detrimental as low frequency acoustics especially those between 800 Hz and 1200 Hz are the frequencies that humans perceive as the loudest noise levels.  Scaling the frequencies measured to those of full scale applications using Strouhal numbers show that frequencies below 1000 Hz in this experiment result in frequencies at the upper limit of the human hearing frequency range.  Low frequency acoustic waves also tend to travel farther and high frequency acoustic waves are more apt to be absorbed by the surrounding atmosphere.
Master of Science
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Schilden, Thomas [Verfasser]. "Numerical Analysis of Wind Tunnel Noise Decomposition Methods in Supersonic Flow / Thomas Schilden." München : Verlag Dr. Hut, 2019. http://d-nb.info/1181514126/34.

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Remillieux, Marcel Christophe. "Aeroacoustic Study of a Model-Scale Landing Gear in a Semi-Anechoic Wind Tunnel." Thesis, Virginia Tech, 2007. http://hdl.handle.net/10919/31674.

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An aeroacoustic study was conducted on a 26%-scale Boeing 777 main landing gear in the Virginia Tech (VT) Anechoic Stability Wind Tunnel. The VT Anechoic Stability Wind Tunnel allowed noise measurements to be carried out using both a 63-elements microphone phased array and a linear array of 15 microphones. The noise sources were identified from the flyover view under various flow speeds and the phased array positioned in both the near and far-field. The directivity pattern of the landing gear was determined using the linear array of microphones. The effectiveness of 4 passive noise control devices was evaluated. The 26%-scale model tested was a faithful reproduction of the full-scale landing gear and included most of the full-scale details with accuracy down to 3 mm. The same landing gear model was previously tested in the original hard-walled configuration of the VT tunnel with the same phased array mounted on the wall of the test section, i.e. near-field position. Thus, the new anechoic configuration of the VT wind tunnel offered a unique opportunity to directly compare, using the same gear model and phased array instrumentation, data collected in hard-walled and semi-anechoic test sections. The main objectives of the present work were (i) to evaluate the validity of conducting aeroacoustic studies in non-acoustically treated, hard-walled wind tunnels, (ii) to test the effectiveness of various streamlining devices (passive noise control) at different flyover locations, and (iii) to assess if phased array measurements can be used to estimate noise reduction. As expected, the results from this work show that a reduction of the background noise (e.g. anechoic configuration) leads to significantly cleaner beamforming maps and allows one to locate noise sources that would not be identified otherwise. By using the integrated spectra for the baseline landing gear, it was found that in the hard-walled test section the levels of the landing gear noise were overestimated. Phased array measurements in the near and far-field positions were also compared in the anechoic configuration. The results showed that straight under the gear, near-field measurements located only the lower-truck noise sources, i.e. noise components located behind the truck were shielded. It was thus demonstrated that near-field, phased-array measurements of the landing gear noise straight under the gear are not suitable. The array was also placed in the far-field, on the rear-arc of the landing gear. From this position, other noise sources such as the strut could be identified. This result demonstrated that noise from the landing gear on the flyover path cannot be characterized by only taking phased array measurement right under the gear. The noise reduction potential of various streamlining devices was estimated from phased array measurements (by integrating the beamforming maps) and using the linear array of individually calibrated microphones. Comparison of the two approaches showed that the reductions estimated from the phased array and a single microphone were in good agreement in the far-field. However, it was found that in the near-field, straight under the gear, phased array measurements greatly overestimate the attenuation.
Master of Science
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Spalt, Taylor B. "Background Noise Reduction in Wind Tunnels using Adaptive Noise Cancellation and Cepstral Echo Removal Techniques for Microphone Array Applications." Thesis, Virginia Tech, 2010. http://hdl.handle.net/10919/34247.

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Two experiments were conducted to investigate Adaptive Noise Cancelling and Cepstrum echo removal post-processing techniques on acoustic data from a linear microphone array in an anechoic chamber. A point source speaker driven with white noise was used as the primary signal. The first experiment included a background speaker to provide interference noise at three different Signal-to-Noise Ratios to simulate noise propagating down a wind tunnel circuit. The second experiment contained only the primary source and the wedges were removed from the floor to simulate reflections found in a wind tunnel environment. The techniques were applicable to both signal microphone and array analysis. The Adaptive Noise Cancellation proved successful in its task of removing the background noise from the microphone signals at SNRs as low as -20 dB. The recovered signals were then used for array processing. A simulation reflection case was analyzed with the Cepstral technique. Accurate removal of the reflection effects was achieved in recovering both magnitude and phase of the direct signal. Experimental data resulted in Cepstral features that caused errors in phase accuracy. A simple phase correction procedure was proposed for this data, but in general it appears that the Cepstral technique is and would be not well suited for all experimental data.
Master of Science
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Wisda, David Martin. "Noise from a Rotor Ingesting Inhomogeneous Turbulence." Thesis, Virginia Tech, 2015. http://hdl.handle.net/10919/52986.

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On-blade hot wire anemometry measurements as well as far field sound measurements at several receiving angles have been previously made for a rotor partially embedded in a boundary layer. The inflow distortion effect on the rotor angle of attack distribution was determined directly from the on-blade measurements, and was found to minimally affect the angle of attack at the blade tips and lower the angle attack in the rotor disk plane as the radial location moves towards the hub. A narrow, sharp increase in angle of attack as the rotor blades approached the wall was also observed, indicating blade interaction with flow reversal. The haystacking pattern, or spectral humps that appear at multiples of the blade passage frequency, was studied for a wide range of advance ratios. At high advance ratios, evidence of vortex shedding from the blade trailing edges was observed. For low advance ratios, the haystacks narrowed, became more symmetric and increased in number. A method of determining the average acoustic signature of an eddy passage through a rotor was developed from time delay aligning multiple microphone signals and eddy passages detected using the continuous wavelet transform. It was found that the eddy passage signatures were similar to a cosine wave with a Gaussian window. It was also found that normalized timescales obtained directly from the eddy passage signatures remained somewhat constant with advance ratio, but increases slightly for fixed free stream velocities with increasing rotor RPM. For advance ratios less than 0.6, the eddy passage signatures were dominated by a tonal component due to rotor ingestion of misaligned flow caused by a boundary layer separation at the wall. This indicates that flow reversal known as the Pirouette Effect is interacting with the rotor blades.
Master of Science
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Yakhina, Gyuzel. "Experimental study of the tonal trailing-edge noise generated by low-reynolds number airfoils and comparison with numerical simulations." Thesis, Lyon, 2017. http://www.theses.fr/2017LYSEC008/document.

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Le bruit tonal rayonné au bord de fuite des profils à faible nombre de Reynolds est un phénomène observé sur les ailes de drones ou micro-drones qui sont utilisés partout dans la vie quotidienne. La diminution de ce bruit va augmenter la survivabilité et l'efficacité des appareils dans le domaine militaire. De plus, cela va augmenter le champ des applications civiles et minimiser la pollution par le bruit. La réduction efficace du bruit est indispensable et, par conséquent, une compréhension complète du processus de rayonnement du bruit tonal du profil est nécessaire. Malgré le fait que des essais dédiés aient été réalisés depuis les années 70, il reste beaucoup de détails à expliquer. Le travail présenté est dédié à une étude expérimentale et analytique du bruit tonal. C'est une partie de collaboration entre l'Ecole Centrale de Lyon et Embry- Riddle Aeronautical University. Le but est de réaliser une caractérisation exhaustive des paramètres acoustiques et aérodynamiques du bruit tonal de bord de fuite d'un profil et de produire une base de données qui pourra être utilisée pour valider les simulations numériques réalisées dans le futur. Le profil symétrique NACA-0012 ainsi que le profil asymétrique SD7003 ont été testés pour une série d'angles d'incidence (de -10° à 10°) dans la soufflerie anéchoïque à jet ouvert de l'Ecole Centrale de Lyon pour des nombres de Reynolds modérés (0.6x105 < Rec < 2.6x105). Les mesures de pression aux parois et de pression acoustique en champ lointain pour différentes configurations ont permis d'observer une structure en escalier de la signature du bruit, de déterminer quelle face du profil a produit le bruit et de distinguer le rôle de la boucle de rétroaction. Des techniques supplémentaires de post-traitement comme l'analyse temps-fréquence ont montré l'existence de plusieurs régimes (un régime de commutation entre deux états, un régime d'une seul fréquence et un régime à plusieurs fréquences) de l'émission de bruit. L'analyse de bi-cohérence a montré qu'il y a des couplages nonlinéaires entre les fréquences. Une étude par l'anémométrie à fil chaud et par des techniques de visualisation de l'écoulement a montré que la formation d'une bulle de décollement est une condition nécessaire mais pas suffisante pour la génération du bruit. De plus, la localisation de la bulle est aussi importante et elle doit être suffisamment proche du bord de fuite. En outre, l'analyse de stabilité linéaire des résultats de simulations numériques a montré que des ondes de Tollmien-Schlichting sont transformées en ondes de Kelvin-Helmholtz dans la zone du décollement. Une prédiction analytique de l'amplitude des fréquences pures émises dans le champ lointain a été effectuée sur la base du modèle d'Amiet en supposant que le champ de pression pariétal est bidimensionnel. Les mesures de pression proches du bord de fuite du profil ont été prises comme données d'entrée. Les amplitudes prédites sont globalement en accord avec les mesures acoustiques. Après l'analyse de tous les résultats la description suivante du processus de rayonnement de sons purs peut être proposée. Les ondes de Tollmien-Schlichting qui se développent initialement dans la couche limite se transforment en ondes de Kelvin-Helmholtz le long de la couche de cisaillement de la bulle de décollement. Au bord de fuite du profil elles sont converties en ondes acoustiques qui forment un couplage fort avec les instabilités de couche limite plus en amont de l'écoulement, pilotant elles-mêmes le déclenchement de ces instabilités
The tonal trailing-edge noise generated by transitional airfoils is a topic of interest because of its wide area of applications. One of them is the Unmanned Air Vehicles operated at low Reynolds numbers which are widely used in our everyday life and have a lot of perspectives in future. The tonal noise reduction will increase the survivability and effectiveness of the devices in military field. Moreover it will enlarge the range of civil use and minimize noise pollution. The effective noise reduction is needed and therefore the complete understanding of the tonal noise generation process is necessary. Despite the fact that investigation of the trailing-edge noise was started since the seventies there are still a lot of details which should be explained. The present work is dedicated to the experimental and analytical investigation of the tonal noise and is a part of the collaboration project between Ecole Centrale de Lyon and Embry-Riddle Aerospace University. The aim is to conduct an exhaustive experimental characterization of the acoustic and aerodynamic parameters of the trailing-edge noise and to produce a data base which can be used for further numerical simulations conducted at Embry-Riddle Aerospace University. A symmetric NACA-0012 airfoil and a slightly cambered SD7003 airfoil at moderate angles of attack (varied from -10° à 10°) were tested in an open-jet anechoic wind tunnel of Ecole Centrale de Lyon at moderate Reynolds numbers (0.6x105 < Rec < 2.6x105). Measurements of the wall pressure and far-field acoustic pressure in different configurations allowed to observe the ladder-type structure of the noise signature, to determine which side produced tones and to distinguish the role of the acoustic feedback loop. Additional post-processing techniques such as time-frequency analysis showed the existence of several regimes (switching regime between two tones, one-tone regime and multiple-tones regime) of noise emission. The bicoherence analysis showed that there are non-linear relationships between tones. The investigation of the role of the separation area by hot-wire anemometry and flow visualization techniques showed that the separation bubble is a necessary but not a suficient condition for the noise generation. Moreover the location of the bubble is also important and should be close enough to the trailing edge. Furthermore the linear stability analysis of accompanying numerical simulation results showed that the Tollmien-Schlichting waves transform to the Kelvin-Helmholtz waves at the separation area. An analytical prediction of the tone levels in the far-field was done using Amiet's model based on the assumption of perfectly correlated sources along the span. The wall-pressure measurements close to the trailing edge were used as an input data. The comparisons of the predicted levels and measured ones showed a good agreement. After analysis of all results the following description of the tonal noise mechanism is proposed. At some initial point of the airfoil the Tollmien-Schlichting instabilities start. They are traveling downstream and continued to Kelvin-Helmholtz waves along the shear-layer of the separation bubble. These waves reach the trailing edge, scatter from it as acoustic waves, which move upstream. The acoustic waves amplify the boundary layer instabilities at some frequencies for which the phases of both motions match and creates the feedback loop needed to sustain the process
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Lemoine, Benoît. "Etude aéroacoustique de configurations génériques de dispositifs hypersustentateurs : approches analytique et expérimentale." Phd thesis, Ecole Centrale de Lyon, 2013. http://tel.archives-ouvertes.fr/tel-00965211.

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Depuis plusieurs décennies, le trafic aérien ne cesse de croître. Ainsi, près de 6 milliards de passagers transitent dans le monde par an. Les objectifs européens à l'horizon 2020 en terme d'émission sonore des aéronefs imposent une réduction de 10 dB par point de mesure par rapport aux aéronefs de l'an 2000. Dans ce contexte, le projet européen VALIANT (VALidation and Improvement of Airframe Noise prediction Tools) a pour but principal de tester, valider et améliorer les codes numériques et les modèles de prédiction du bruit de cellule (trains d'atterrissage + voilure) sur des géométries simplifiées afin de disposer de cas tests pour les recherches futures. L'objectif de la thèse, associé à la contribution de l'ECL dans ce projet, est de créer des bases de données expérimentales fiables sur des systèmes à deux éléments - bec/aile et aile/volet - et de modéliser analytiquement le bruit issu de tels systèmes. La thèse s'est concentrée sur un système aile/volet non porteur et parallèle dans un écoulement de soufflerie à veine ouverte, en configuration d'alignement ou de recouvrement partiel, menant à de possibles interactions aérodynamiques et/ou acoustiques. Les mesures ont été faites pour différentes vitesses d'écoulement (30 − 100 m~s), avec une attention particulière à 50 m~s (M0 ∼ 0, 15). Le taux de turbulence de l'écoulement incident est modifiable par l'ajout d'une grille de turbulence à maille large placée dans la section de sortie du convergent. Les résultats aérodynamiques (fil chaud, pression en paroi) ont révélé la présence d'une forte interaction lorsque la distance entre les deux corps est de l'ordre de grandeur de la couche limite turbulente au bord de fuite de l'aile. De plus, le couplage acoustique a lieu lorsque la longueur de recouvrement est positive ou nulle. Des mesures de localisation de sources menées par l'ONERA/DSNA ont permis de valider les mesures de champ lointain en confirmant l'absence de sources de bruit d'installation en dessous de 10 kHz. Par ailleurs, des comparaisons avec les simulations numériques donnent de bons accords. Du point de vue analytique, le problème mathématique de deux plaques planes en recouvrement partiel dans un écoulement uniforme a été posé et une réduction bidimensionnelle a été justifiée. Le problème n'ayant pas de solution exacte, plusieurs modèles issus de la littérature - théories de Howe et d'Amiet - ont été étudiés. Les plus pertinents ont été confrontés aux résultats expérimentaux, révélant les limites asymptotiques de ces modèles. Un modèle original est alors proposé pour la géométrie du problème posé, sans hypothèse restrictive. La démarche est basée sur une procédure de diffraction itérative permettant de prendre en compte la proximité des deux corps et utilisant la fonction de Green exacte du demi-plan en écoulement uniforme. Le modèle prédit des comportements qualitatifs angle/fréquence proches des résultats expérimentaux. La prise en compte de la statistique des rafales incidentes reste néanmoins à effectuer afin de procéder à des comparaisons quantitatives. Une campagne expérimentale complémentaire avec une marche descendante permet de mettre en évidence les écoulements de cavité arrière d'une aile, plus proche de la réalité. De même, des mesures sur une configuration bec/aile a été testée et la prise en compte de la déflexion du jet de la soufflerie pour la réfraction des ondes sonores par la couche de cisaillement a été proposée.
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Books on the topic "Wind tunnel noise"

1

Hoad, Danny R. Rotor performance characteristics from an aeroacoustics helicopter wind-tunnel test program. Hampton, Va: Langley Research Center, 1986.

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Abrahamson, A. Louis. An evaluation of proposed acoustic treatments for the NASA LaRC 4 x 7 meter wind tunnel. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1985.

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Soderman, Paul T. J-85 jet engine noise measured in the ONERA S1 Wind Tunnel and extrapolated to far field. Moffett Field, Calif: Ames Research Center, 1991.

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Soderman, Paul T. J-85 jet engine noise measured in the ONERA S1 wind tunnel and extrapolated to far field. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1991.

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Soderman, Paul T. J-85 jet engine noise measured in the ONERA S1 wind tunnel and extrapolated to far field. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1991.

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Martin, R. M. Acoustic measurements from a rotor blade-vortex interaction noise experiment in the German-Dutch Wind Tunnel (DNW). Hampton, Va: Langley Research Center, 1988.

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Soderman, Paul T. Sources and levels of background noise in the NASA Ames 40- by 80-foot wind tunnel: A status report. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1988.

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Block, P. J. W. Directory and trends of noise generated by a propeller in a wake. Hampton, Va: Langley Research Center, 1986.

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Fears, Scott P. Low-speed wind-tunnel investigation of a porous forebody and nose strakes for yaw control of a multirole fighter aircraft. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

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Fears, Scott P. Low-speed wind-tunnel investigation of a porous forebody and nose strakes for yaw control of a multirole fighter aircraft. Hampton, Va: Langley Research Center, 1995.

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Book chapters on the topic "Wind tunnel noise"

1

Yinzhi, He, Zhigang Yang, and Yigang Wang. "Wind Noise Testing at Shanghai Automotive Wind Tunnel Center." In Lecture Notes in Electrical Engineering, 571–78. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-33832-8_44.

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He, Yinzhi, Z. Yang, and Y. Wang. "Wind noise testing at the full scale aeroacoustic wind tunnel of Shanghai Automotive Wind Tunnel Center." In Proceedings, 1369–78. Wiesbaden: Springer Fachmedien Wiesbaden, 2014. http://dx.doi.org/10.1007/978-3-658-05130-3_97.

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Wang, Jian, Wenjiang Wang, and Kangle Xu. "Acoustical Wind Tunnel Studies of Landing Gear Noise." In Fluid-Structure-Sound Interactions and Control, 69–75. Berlin, Heidelberg: Springer Berlin Heidelberg, 2015. http://dx.doi.org/10.1007/978-3-662-48868-3_11.

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Uda, T., N. Yamazaki, T. Kitagawa, K. Nagakura, and Y. Wakabayashi. "Estimation of Aerodynamic Bogie Noise Through Field and Wind Tunnel Tests." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 377–87. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-73411-8_28.

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Deng, Hai, Yigang Wang, Qiliang Li, Zhe Shen, Yang Gao, and Jin Lisheng. "Wind Tunnel Tests on Aerodynamic Noise from the Head Car of a High-speed Train." In Lecture Notes in Electrical Engineering, 163–76. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-16-5429-9_12.

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Kangle, Xu, and Wang Jian. "The Spectrum and Directivity Extrapolation Method of an Acoustic Wind Tunnel Test for a Scaled Airframe Noise." In Fluid-Structure-Sound Interactions and Control, 77–81. Berlin, Heidelberg: Springer Berlin Heidelberg, 2015. http://dx.doi.org/10.1007/978-3-662-48868-3_12.

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Sawamura, Yoichi, Toki Uda, Toshiki Kitagawa, Hiroshi Yokoyama, and Akiyoshi Iida. "Measurement and Reduction of the Aerodynamic Bogie Noise Generated by High-Speed Trains in Terms of Wind Tunnel Testing." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 73–80. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-70289-2_5.

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Pate, Samuel R. "Dominance of “Noise” on Boundary Layer Transition in Conventional Wind Tunnels — a Place for the “Quiet” Ballistic Range in Future Studies." In Advances in Soil Science, 77–87. New York, NY: Springer New York, 1990. http://dx.doi.org/10.1007/978-1-4612-3430-2_11.

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Yokoi, Yoshifumi. "Experimental Study of Internal Flow Noise Measurement by Use of a Suction Type Low Noise Wind Tunnel." In Wind Tunnel Designs and Their Diverse Engineering Applications. InTech, 2013. http://dx.doi.org/10.5772/53828.

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Medved, B., and D. Prica. "An Experimental Means of Reducing the Overall Aerodynamic Noise Level in a 0.25 m Transonic Wind Tunnel Test Section." In Zeitschrift für Angewandte Mathematik und Mechanik Volume 66, Number 4, 243–45. De Gruyter, 1986. http://dx.doi.org/10.1515/9783112550922-107.

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Conference papers on the topic "Wind tunnel noise"

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Baudet, Guillaume. "Wind Noise Source Identification by Inverse Method in Wind Tunnel Test." In Noise and Vibration Conference and Exhibition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2017. http://dx.doi.org/10.4271/2017-01-1784.

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Barajas-Olalde, C., and A. Jeffreys. "Seismic Wind Noise Experiments Using a Portable Wind Tunnel." In 76th EAGE Conference and Exhibition 2014. Netherlands: EAGE Publications BV, 2014. http://dx.doi.org/10.3997/2214-4609.20141583.

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Chen, Kuo-Huey, James Johnson, Urs Dietschi, and Bahram Khalighi. "Automotive Mirror Wind Noise Simulations and Wind Tunnel Measurements." In 14th AIAA/CEAS Aeroacoustics Conference (29th AIAA Aeroacoustics Conference). Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-2906.

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Hofmann, Lorenz M., Djamel Bouzit, Keith W. Murawski, Keng D. Hsueh, Miles Janicki, and Michael P. Haffey. "Artificial Reduction of Wind Tunnel Background Noise in Vehicle Wind Noise Testing." In International Congress & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1998. http://dx.doi.org/10.4271/980390.

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Ogata, N., N. Iida, and Y. Fujii. "Nissan's Low-Noise Full-Scale Wind Tunnel." In SAE International Congress and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1987. http://dx.doi.org/10.4271/870250.

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Stoker, R., K. Ahuja, and J. Hsu. "Separation of wind-tunnel background noise and wind noise from automobile interior measurements." In Aeroacoustics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-1763.

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Thompson, Mark, Simon Watkins, and Jongman Kim. "Wind-Tunnel and On-Road Wind Noise: Comparison and Replication." In SAE 2013 World Congress & Exhibition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2013. http://dx.doi.org/10.4271/2013-01-1255.

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Roditcheva, Olga, Lennart Carl Lofdahl, Simone Sebben, Pär Harling cEng, and Holger Bernhardsson. "On the Possibilities and Limitations of Wind Noise Testing in the Aerodynamical Wind Tunnel at Volvo Cars." In 9th International Styrian Noise, Vibration & Harshness Congress: The European Automotive Noise Conference. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2016. http://dx.doi.org/10.4271/2016-01-1807.

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Simpson, M., G. Mathur, B. Tran, C. Chin, J. Lee, and M. Sundquist. "Supersonic wind tunnel tests of panel noise transmission." In 5th AIAA/CEAS Aeroacoustics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-1962.

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Drobietz, Roger, and Ingo Borchers. "Generic Wind Tunnel Study on Side Edge Noise." In 12th AIAA/CEAS Aeroacoustics Conference (27th AIAA Aeroacoustics Conference). Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-2509.

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Reports on the topic "Wind tunnel noise"

1

Grossir, Guillaume. On the design of quiet hypersonic wind tunnels. Von Karman Institute for Fluid Dynamics, December 2020. http://dx.doi.org/10.35294/tm57.

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This document presents a thorough literature review on the development of hypersonic quiet tunnels. The concept of boundary layer transition in high-speed flows is presented first. Its consequences on the free-stream turbulence levels in ground facilities are reviewed next, demonstrating that running boundary layers along the nozzle walls must remain laminar for quiet operation. The design key points that enable laminar boundary layers and hypersonic operation with low free-stream noise levels are then identified and discussed. The few quiet facilities currently operating through the world are also presented, along with their design characteristics and performances. The expected characteristics and performances of a European quiet tunnel are also discussed, along with flow characterization methodologies and different measurement techniques. It is finally shown that the required expertise to establish the first European quiet hypersonic wind tunnel is mostly at hand.
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Tuchiya, Masaki, Tsuyoshi Yamashita, Niels V. B\atgholm, Toshikazu Satoh, and Masateru Kimura. Aero-Acoustic Noise Measurement of Vehicle Using Surface Microphone in Wind Tunnel. Warrendale, PA: SAE International, May 2005. http://dx.doi.org/10.4271/2005-08-0170.

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