Relevant bibliographies by topics / Trailing-edge noise prediction

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Trailing-edge noise prediction'

Author: Grafiati
Published: 4 June 2021
Last updated: 1 February 2022

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Journal articles on the topic "Trailing-edge noise prediction"

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Lyu, B., M. Azarpeyvand, and S. Sinayoko. "Prediction of noise from serrated trailing edges." Journal of Fluid Mechanics 793 (March 18, 2016): 556–88. http://dx.doi.org/10.1017/jfm.2016.132.

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A new analytical model is developed for the prediction of noise from serrated trailing edges. The model generalizes Amiet’s trailing-edge noise theory to sawtooth trailing edges, resulting in a complicated partial differential equation. The equation is then solved by means of a Fourier expansion technique combined with an iterative procedure. The solution is validated through comparison with the finite element method for a variety of serrations at different Mach numbers. The results obtained using the new model predict noise reduction of up to 10 dB at 90$^{\circ }$ above the trailing edge, which is more realistic than predictions based on Howe’s model and also more consistent with experimental observations. A thorough analytical and numerical analysis of the physical mechanism is carried out and suggests that the noise reduction due to serration originates primarily from interference effects near the trailing edge. A closer inspection of the proposed mathematical model has led to the development of two criteria for the effectiveness of the trailing-edge serrations, consistent but more general than those proposed by Howe. While experimental investigations often focus on noise reduction at 90$^{\circ }$ above the trailing edge, the new analytical model shows that the destructive interference scattering effects due to the serrations cause significant noise reduction at large polar angles, near the leading edge. It has also been observed that serrations can significantly change the directivity characteristics of the aerofoil at high frequencies and even lead to noise increase at high Mach numbers.
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Li, Sicheng (Kevin), and Seongkyu Lee. "Prediction of Rotorcraft Broadband Trailing-Edge Noise and Parameter Sensitivity Study." Journal of the American Helicopter Society 65, no. 4 (2020): 1–14. http://dx.doi.org/10.4050/jahs.65.042006.

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This paper investigates the effects of rotorcraft design and operating parameters on trailing-edge noise. A rotor trailing-edge noise prediction method is first developed where the aerodynamics and the turbulence wall pressure spectrum near the trailing edge on airfoils are predicted by a combination of the standard blade element momentum theory , a viscous boundary-layer panel method, and a recently developed empirical wall pressure spectrum model. The coordinate transformations are combined with the Amiet model to predict far-field noise. Compared to experimental data, the validation of this method demonstrates its advantages and validity for airfoil and rotorcraft broadband noise predictions. Then, this method is used to study the effects of rotorcraft design and operating parameters on rotor trailing-edge noise. It is found that helicopter broadband noise scales with the 4.5th to 5.0th power of the tip Mach number in which the range is determined by the typical helicopter collective pitch angle in operation. Detailed trend analyses of noise levels as a function of frequency are presented in terms of the collective pitch angle, twist angle, rotor solidity, rotor radius, disk loading, and number of blades. It is found that the collective pitch angle, twist angle, and chord length make noticeable impacts on low- and midfrequency noise. Finally, a semianalytic model is presented to predict the directivity and geometric attenuation of rotor trailing-edge noise.
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Han, Dongyeon, Jihoon Choi, and Soogab Lee. "Prediction Method for Trailing-edge Serrated Wind Turbine Noise." New & Renewable Energy 16, no. 2 (2020): 1–13. http://dx.doi.org/10.7849/ksnre.2020.2019.

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Stalnov, Oksana, Paruchuri Chaitanya, and Phillip F. Joseph. "Towards a non-empirical trailing edge noise prediction model." Journal of Sound and Vibration 372 (June 2016): 50–68. http://dx.doi.org/10.1016/j.jsv.2015.10.011.

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Rozenberg, Yannick, Michel Roger, and Stéphane Moreau. "Fan Blade Trailing‐Edge Noise Prediction Using RANS Simulations." Journal of the Acoustical Society of America 123, no. 5 (2008): 3688. http://dx.doi.org/10.1121/1.2935064.

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Lyu, B., A. P. Dowling, and I. Naqavi. "Prediction of installed jet noise." Journal of Fluid Mechanics 811 (December 6, 2016): 234–68. http://dx.doi.org/10.1017/jfm.2016.747.

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A semianalytical model for installed jet noise is proposed in this paper. We argue and conclude that there exist two distinct sound source mechanisms for installed jet noise, and the model is therefore composed of two parts to account for these different sound source mechanisms. Lighthill’s acoustic analogy and a fourth-order space–time correlation model for the Lighthill stress tensor are used to model the sound induced by the equivalent turbulent quadrupole sources, while the trailing-edge scattering of near-field evanescent instability waves is modelled using Amiet’s approach. A non-zero ambient mean flow is taken into account. It is found that, when the rigid surface is not so close to the jet as to affect the turbulent flow field, the trailing-edge scattering of near-field evanescent waves dominates the low-frequency amplification of installed jet noise in the far-field. The high-frequency noise enhancement on the reflected side is due to the surface reflection effect. The model agrees well with experimental results at different observer angles, apart from deviations caused by the mean-flow refraction effect at high frequencies at low observer angles.
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Oerlemans, S., and J. G. Schepers. "Prediction of Wind Turbine Noise and Validation against Experiment." International Journal of Aeroacoustics 8, no. 6 (2009): 555–84. http://dx.doi.org/10.1260/147547209789141489.

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A semi-empirical prediction method for trailing edge noise is applied to calculate the noise from two modern large wind turbines. The prediction code only needs the blade geometry and the turbine operating conditions as input. Using detailed acoustic array and directivity measurements, a thorough validation of the predictions is carried out. The predicted noise source distribution in the rotor plane (as a function of frequency and observer position) shows the same characteristics as in the experiments: due to trailing edge noise directivity and convective amplification, practically all noise (emitted to the ground) is produced during the downward movement of the blades, causing an amplitude modulation of broadband aerodynamic blade noise at the blade passing frequency (‘swish’). Good agreement is also found between the measured and predicted spectra, in terms of levels and spectral shape. For both turbines, the deviation between predicted and measured overall sound levels (as a function of rotor power) is less than 1–2 dB, which is smaller than the scatter in the experimental data. Using a smoothed analytical trailing edge noise directivity function, the turbine noise directivity is predicted within 1–2 dB, and the swish amplitude in different directions within 1 dB. This semi-empirical directivity function shows similar characteristics as the theoretical directivity function for a flat plate, except for regions close to the plane of the blade. The validated prediction code is then applied to calculate noise footprints of the wind turbine as a function of rotor azimuth. These footprints show that for cross-wind directions the average level is lower than in the up- and downwind directions, but the variation in level is larger. Even at large distance, swish amplitudes up to 5 dB can be expected for cross-wind directions.
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SANDBERG, RICHARD D., and NEIL D. SANDHAM. "Direct numerical simulation of turbulent flow past a trailing edge and the associated noise generation." Journal of Fluid Mechanics 596 (January 17, 2008): 353–85. http://dx.doi.org/10.1017/s0022112007009561.

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Direct numerical simulations (DNS) are conducted of turbulent flow passing an infinitely thin trailing edge. The objective is to investigate the turbulent flow field in the vicinity of the trailing edge and the associated broadband noise generation. To generate a turbulent boundary layer a short distance from the inflow boundary, high-amplitude lifted streaks and disturbances that can be associated with coherent outer-layer vortices are introduced at the inflow boundary. A rapid increase in skin friction and a decrease in boundary layer thickness and pressure fluctuations is observed at the trailing edge. It is demonstrated that the behaviour of the hydrodynamic field in the vicinity of the trailing edge can be predicted with reasonable accuracy using triple-deck theory if the eddy viscosity is accounted for. Point spectra of surface pressure difference are shown to vary considerably towards the trailing edge, with a significant reduction of amplitude occurring in the low-frequency range. The acoustic pressure obtained from the DNS is compared with predictions from two- and three-dimensional acoustic analogies and the classical trailing-edge theory of Amiet. For low frequencies, two-dimensional theory succeeds in predicting the acoustic pressure in the far field with reasonable accuracy due to a significant spanwise coherence of the surface pressure difference and predominantly two-dimensional sound radiation. For higher frequencies, however, the full three-dimensional theory is required for an accurate prediction of the acoustic far field. DNS data are used to test some of the key assumptions invoked by Amiet for the derivation of the classical trailing-edge theory. Even though most of the approximations are shown to be reasonable, they collectively lead to a deviation from the DNS results, in particular for higher frequencies. Moreover, because the three-dimensional acoustic analogy does not provide significantly improved results, it is suggested that some of the discrepancies can be attributed to the approach of evaluating the far-field sound using a Kirchhoff-type integration of the surface pressure difference.
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Lau, Alex Siu Hong, Jae Wook Kim, Jeremy Hurault, Tomas Vronsky, and Phillip Joseph. "Aerofoil trailing-edge noise prediction models for wind turbine applications." Wind Energy 20, no. 10 (2017): 1727–52. http://dx.doi.org/10.1002/we.2119.

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Cozza, I. F., A. Iob, and R. Arina. "Broadband trailing-edge noise prediction with a stochastic source model." Computers & Fluids 57 (March 2012): 98–109. http://dx.doi.org/10.1016/j.compfluid.2011.12.011.

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Dissertations / Theses on the topic "Trailing-edge noise prediction"

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Spitz, Nicolas. "Prediction of Trailing Edge Noise from Two-Point Velocity Correlations." Thesis, Virginia Tech, 2005. http://hdl.handle.net/10919/32637.

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This thesis presents the implementation and validation of a new methodology developed by Glegg et al. (2004) for solving the trailing edge noise problem. This method is based on the premises that the noise produced by a surface can be computed by the integral of the cross product between the velocity and vorticity fields, of the boundary layer and shed vorticity (Howe (1978)). To extract the source terms, proper orthogonal decomposition is applied to the velocity cross spectrum to extract modes of the unsteady velocity and vorticity. The new formulation of the trailing edge noise problem by Glegg et al. (2004) is attractive because it applies to the high frequencies of interest but does not require an excessive computational effort. Also, the nature of the formulation permits the identification of the modes producing the noise and their associated velocity fluctuations as well as the regions of the boundary layer responsible for the noise production. The source terms were obtained using the direct numerical simulation of a turbulent channel flow by Moser et al. (1998). Two-point velocity and vorticity statistics of this data set were obtained by averaging 41 instantaneous fields. For comparisons purposes, experimental boundary layer data by Adrian et al. (2000) was chosen. Statistical reduction of 50 velocity fields obtained by particle image velocimetry was performed and analysis of the two-point correlation function showed features similar to the DNS data case. Also, proper orthogonal decomposition revealed identical dominant modes and eddy structures in the flow, therefore justifying considering the channel flow as an external boundary layer for noise calculations. Comparison of noise predictions with experimental data from Brooks et al. (1989) showed realistic results with the largest discrepancies, on the order of 5 dB, occurring at the lowest frequencies. The DNS results are least applicable at these frequencies, since these correspond to the longest streamwise lengthscales, which are the most affected by the periodicity conditions used in the DNS and also are the least representative of the turbulence in an external boundary layer flow. Most of the noise was shown to be produced by low-frequency streamwise velocity modes in the bottom 10% of the boundary layer and locations closest to the wall. Only 6 modes were required to obtain noise levels within 1 dB of the total noise. Finally, the method for predicting spatial velocity correlation from Reynolds stress data in wake flows, originally developed by Devenport et al. (1999, 2001) and Devenport and Glegg (2001), was adapted to boundary-layer type flows. This method, using Reynolds stresses and the prescription of a lengthscale to extrapolate the full two-point correlation, was shown to produce best results for a lengthscale prescribed as proportional to the turbulent macroscale. Noise predictions using modeled two-point statistics showed good agreement with the DNS inferred data in all but frequency magnitude, a probable consequence of the modeling of the correlation function in the streamwise direction. Other quantities associated to noise were seen to be similar to the ones obtained using the DNS.<br>Master of Science
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Nguyen, Danny. "Validation and Improvement of the TNO Model for Trailing Edge Noise Prediction." Thesis, University of California, Davis, 2018. http://pqdtopen.proquest.com/#viewpdf?dispub=10933376.

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<p> The TNO model, a trailing edge noise prediction method, is validated, modified, and analyzed for various input formats. Two different methods are used to calculate the flow field for this model: Reynolds averaged Navier-Stokes (RANS) and a viscous panel method, XFOIL. It is found that the RANS-based TNO model show good agreement with the experiments but the XFOIL-based TNO was found to overpredict the turbulence kinetic energy and, consequently, the sound pressure level. A modification is made in the XFOIL-based TNO model by substituting Prandtl's mixing length hypothesis from the original model with a new blended model consisting of the mixing length hypothesis and the Cebeci-Smith eddy viscosity model. Twenty-six different test cases are tested with airfoils: NACA 0012, NACA 0015, NACA 64-618, NACA 64<sub>3</sub>-418, and DU 96-w-180. RANS input to the TNO model is able to predict the sound pressure spectrum to within 3 dB for the frequency range of 800Hz to 2000Hz in 16 of the 26 cases. The new blended model is found to show clear improvements to the prediction for 14 out of the 26 cases when compared to the original XFOIL input. Moreover, the new XFOIL input was able to predict sound pressure level to within 3 dB for 14 of the 26 cases. Overall, the new proposed model improves the prediction for the XFOIL-based TNO model.</p><p>
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Nigro, David. "Prediction of broadband aero and hydrodynamic noise : derivation of analytical models for low frequency." Thesis, University of Manchester, 2017. https://www.research.manchester.ac.uk/portal/en/theses/prediction-of-broadband-aero-and-hydrodynamic-noise-derivation-of-analytical-models-for-low-frequency(25bb8835-9cf8-488a-acc0-677a53122801).html.

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In this thesis we explore several topics with applications to both aero and hydroacoustics. Due to the much larger speed of sound in water compared to in air, several of the approximations used in aeroacoustics are not applicable underwater over the range of frequencies of interest. Specifically, we study the finite-chord effects on two broadband noise mechanisms: the trailing edge noise and the ingested noise problems. We start by investigating the acoustic wave diffraction by a finite rigid plate using three different methods. We compare the behaviour of the different solutions as a function of the reduced acoustic wavenumber. Our results reveal that the Mathieu function expansion is the most appropriate method as long as the reduced acoustic wavenumber is not too large. Finally, we show how the Mathieu functions can be used to build a Green's function tailored to an elliptic cylinder of arbitrary aspect ratio without relying on addition theorems. The results obtained in chapter two motivated the search for an exact solution to the trailing edge noise problem using a Mathieu function expansion. It is shown that the approximate methods used in aeroacoustics are not accurate enough for reduced acoustic wavenumbers less than unity, and for all wavenumbers near cut-off. Furthermore it is shown that, even at low Mach numbers, it is crucial to take into account the effects of convection at low frequency. Finally Lighthill's analogy is used, combined with the tailored Green's function introduced previously, to recover the two asymptotic Mach number scalings of the acoustic power for a flat plate at high frequency and low frequency. In chapter four, we introduce a novel method to solve the ingested noise problem by decomposing the pressure field into a singular part whose functional form can easily be found, and a regular part that we express using a Mathieu function expansion. It was found that finite-chord effects do have a strong impact for reduced acoustic wavenumbers less than unity, and for all wavenumbers near cut-off. The following chapter focuses on the trailing edge noise mechanism and details how the theory for a single stationary aerofoil can be applied to a rotating propeller. Due to the general geometry of a blade, we extended Amiet's model to take into account a mean flow misaligned with the blade chordline. Different semi-analytical models of wall pressure spectra are introduced and compared. We make extensive use of Brooks' data for a NACA 0012 aerofoil to obtain realistic inputs in the semi-analytical models. Finally, we introduce and compare two models of rotating blade trailing edge noise. The effects of both the angle of attack and the number of strips are then investigated. The final chapter is distinct from the rest of the thesis. We propose a model for studying the low Mach number flow noise from a 2D circular cylinder with small roughness. The method is based on using the Green's function tailored to a smooth cylinder in Curle's acoustic analogy. It was found that the main source of noise was the tonal low frequency scattering by the smooth geometry. However, it is suggested that roughness elements might be the dominant source of noise at higher frequency.
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Junior, Joseph Youssif Saab. "Trailing-edge noise: development and application of a noise prediction tool for the assessment and design of wind turbine airfoils." Universidade de São Paulo, 2016. http://www.teses.usp.br/teses/disponiveis/3/3150/tde-14032017-140101/.

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This report concerns the research, design, implementation and application of an airfoil trailing-edge noise prediction tool in the development of new, quieter airfoil for large-size wind turbine application. The tool is aimed at enabling comparative acoustic performance assessment of airfoils during the early development cycle of new blades and rotors for wind turbine applications. The ultimate goal is to enable the development of quieter wind turbines by the Wind Energy Industry. The task was accomplished by developing software that is simultaneously suitable for comparative design, computationally efficient and user-friendly. The tool was integrated into a state-of-the-art wind turbine design and analysis code that may be downloaded from the web, in compiled or source code form, under general public licensing, at no charge. During the development, an extensive review of the existing airfoil trailing-edge noise prediction models was accomplished, and the semi-empirical BPM model was selected and modified to cope with generic airfoil geometry. The intrinsic accuracy of the original noise prediction model was evaluated as well as its sensitivity to the turbulence length scale parameter, with restrictions imposed accordingly. The criterion allowed comparison of performance of both CFD-RANS and a hybrid solver (XFLR5) on the calculation of the turbulent boundary layer data, with the eventual adjustment and selection of the latter. After all the elements for assembling the method had been selected and the code specified, a collaboration project was made effective between Poli-USP and TU-Berlin, which allowed the seamless coupling of the new airfoil TE noise module, \"PNoise\", to the popular wind turbine design/analysis integrated environment, \"QBlade\". After implementation, the code calculation routines were thoroughly verified and then used in the development of a family of \"silent profiles\" with good relative acoustic and aerodynamic performance. The sample airfoil development study closed the initial design cycle of the new tool and illustrated its ability to fulfill the originally intended purpose of enabling the design of new, quieter blades and rotors for the advancement of the Wind Energy Industry with limited environmental footprint.<br>Este trabalho descreve a pesquisa de elementos iniciais, o projeto, a implantação e a aplicação de uma ferramenta de predição de ruído de bordo de fuga, no desenvolvimento de aerofólios mais silenciosos para turbinas eólicas de grande porte. O objetivo imediato da ferramenta é permitir a comparação de desempenho acústico relativo entre aerofólios no início do ciclo de projeto de novas pás e rotores de turbinas eólicas. O objetivo mais amplo é possibilitar o projeto de turbinas eólicas mais silenciosas, mas de desempenho aerodinâmico preservado, pela indústria da Energia Eólica. A consecução desses objetivos demandou o desenvolvimento de uma ferramenta que reunisse, simultaneamente, resolução comparativa, eficiência computacional e interface amigável, devido à natureza iterativa do projeto preliminar de um novo rotor. A ferramenta foi integrada a um ambiente avançado de projeto e análise de turbinas eólicas, de código aberto, que pode ser livremente baixado na Web. Durante a pesquisa foi realizada uma ampla revisão dos modelos existentes para predição de ruído de bordo de fuga, com a seleção do modelo semi-empírico BPM, que foi modificado para lidar com geometrias genéricas. A precisão intrínseca do modelo original foi avaliada, assim como sua sensibilidade ao parâmetro de escala de turbulência transversal, com restrições sendo impostas a esse parâmetro em decorrência da análise. Esse critério permitiu a comparação de resultados de cálculo provenientes de método CFD-RANS e de método híbrido (XFLR5) de solução da camada limite turbulenta, com a escolha do último. Após a seleção de todos os elementos do método e especificação do código, uma parceria foi estabelecida entre a Poli-USP e a TU-Berlin, que permitiu a adição de um novo módulo de ruído de bordo de fuga, denominado \"PNoise\", ao ambiente de projeto e análise integrado de turbinas eólicas \"QBlade\". Após a adição, as rotinas de cálculo foram criteriosamente verificadas e, em seguida, aplicadas ao desenvolvimento de aerofólios mais silenciosos, com bons resultados acústicos e aerodinâmicos relativos a uma geometria de referência. Esse desenvolvimento ilustrou a capacidade da ferramenta de cumprir a missão para a qual foi inicialmente projetada, qual seja, permitir à Indústria desenvolver pás mais silenciosas que irão colaborar com o avanço da energia eólica através da limitação do seu impacto ambiental.
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Erwin, James Paul Brentner Kenneth S. Morris Philip J. "Trailing edge noise prediction using the nonlinear disturbance equations." 2009. http://etda.libraries.psu.edu/theses/approved/WorldWideIndex/ETD-3426/index.html.

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Books on the topic "Trailing-edge noise prediction"

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J, Shamroth S., Langley Research Center, and Scientific Research Associates, eds. On the application of a hairpin vortex model of wall turbulence to trailing edge noise prediction. National Aeronautics and Space Administration, Langley Research Center, 1985.

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Nicolas, Spitz, and NASA Glenn Research Center, eds. Predicting modes of the unsteady vorticity field near the trailing edge of a blade. National Aeronautics and Space Administration, Glenn Research Center, 2003.

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Nicolas, Spitz, and NASA Glenn Research Center, eds. Predicting modes of the unsteady vorticity field near the trailing edge of a blade. National Aeronautics and Space Administration, Glenn Research Center, 2003.

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Book chapters on the topic "Trailing-edge noise prediction"

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Karimi, M., P. Croaker, and N. Kessissoglou. "Trailing-Edge Noise Prediction Using a Periodic BEM Technique." In Fluid-Structure-Sound Interactions and Control. Springer Berlin Heidelberg, 2015. http://dx.doi.org/10.1007/978-3-662-48868-3_6.

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Suryadi, Alexandre. "Prediction of Trailing-Edge Noise for Separated Turbulent Boundary Layers." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-25253-3_73.

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Schuele, Chan Yong, and Karl-Stéphane Rossignol. "A Separated Flow Model for Semi-Empirical Prediction of Trailing Edge Noise." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-03158-3_65.

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Rossian, Lennart, Roland Ewert, and Jan W. Delfs. "Prediction of Airfoil Trailing Edge Noise Reduction by Application of Complex Porous Material." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-64519-3_58.

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Conference papers on the topic "Trailing-edge noise prediction"

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Sinayoko, Samuel, Mahdi Azarpeyvand, and Benshuai Lyu. "Trailing edge noise prediction for rotating serrated blades." In 20th AIAA/CEAS Aeroacoustics Conference. American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-3296.

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Rozenberg, Yannick, Stephane Moreau, Manuel Henner, and Scott Morris. "Fan Trailing-Edge Noise Prediction Using RANS Simulations." In 16th AIAA/CEAS Aeroacoustics Conference. American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-3720.

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Erwin, James, Philip Morris, and Kenneth Brentner. "Trailing-Edge Noise Prediction Using the Nonlinear Disturbance Equations." In 47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition. American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-272.

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Kamruzzaman, Mohammad, Dimitrios Bekiropoulos, Alexander Wolf, Thorsten Lutz, and Ewald Kraemer. "Rnoise: A RANS Based Airfoil Trailing-edge Noise Prediction Model." In 20th AIAA/CEAS Aeroacoustics Conference. American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-3305.

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Casper, J., and F. Farassat. "Trailing Edge Noise Prediction Based on a New Acoustic Formulation." In 8th AIAA/CEAS Aeroacoustics Conference & Exhibit. American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-2477.

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Christiansen, Monica, Kenneth Brentner, and Philip Morris. "Trailing-Edge Noise Prediction Using the Non-Linear Disturbance Equations." In 17th AIAA/CEAS Aeroacoustics Conference (32nd AIAA Aeroacoustics Conference). American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-2797.

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Wagner, Georges A., Mathieu Deuse, Simon J. Illingworth, and Richard D. Sandberg. "Resolvent analysis-based pressure modeling for trailing edge noise prediction." In 25th AIAA/CEAS Aeroacoustics Conference. American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-2720.

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Shi, Yuejun, and Denghui Qin. "SAS-based Airfoil Trailing Edge Noise Prediction in Stall Conditions." In AIAA AVIATION 2020 FORUM. American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-2744.

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Wagner, Georges, and Richard Sandberg. "Resolvent Method Surface Pressures for Airfoil Trailing-Edge Noise Prediction." In 22nd Australasian Fluid Mechanics Conference AFMC2020. The University of Queensland, 2020. http://dx.doi.org/10.14264/6a41fdc.

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Winkler, Julian, Thomas Carolus, and Stéphane Moreau. "Airfoil Trailing-Edge Blowing: Broadband Noise Prediction from Large-Eddy Simulation." In 15th AIAA/CEAS Aeroacoustics Conference (30th AIAA Aeroacoustics Conference). American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-3200.

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Reports on the topic "Trailing-edge noise prediction"

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Chyczewski, Thomas S., Philip J. Morris, and Lyle N. Long. Trailing Edge Noise Prediction: Large-Eddy Simulation of Wall Bounded Shear Flow Using the Nonlinear Disturbance Equations. Defense Technical Information Center, 2000. http://dx.doi.org/10.21236/ada382346.

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