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Journal articles on the topic 'Aero-acoustics'

Author: Grafiati

Published: 4 June 2021

Last updated: 7 July 2024

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1

HIRSCHBERG, A., J. GILBERT, A. P. J. WIJNANDS, and A. M. C. VALKERING. "Musical aero-acoustics of the clarinet." Le Journal de Physique IV 04, no. C5 (May 1994): C5–559—C5–568. http://dx.doi.org/10.1051/jp4:19945120.

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2

Gabard, G., R. J. Astley, P. Gamallo, and G. Kennedy. "Physics-based computational methods for aero-acoustics." Procedia Engineering 6 (2010): 183–92. http://dx.doi.org/10.1016/j.proeng.2010.09.020.

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3

Allen, John S., and Kevin 0'Rourke. "Advances in aero-acoustics of flying beetles." Journal of the Acoustical Society of America 152, no. 4 (October 2022): A276. http://dx.doi.org/10.1121/10.0016255.

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An understanding of the acoustics of invasive species of beetles is needed for potential detection and tracking methods in agricultural monitoring. However, the underlying mechanisms of sound generation are not well understood, especially with respect to the higher harmonic sounds. The Coconut Rhinoceros Beetle (Oryctes rhinoceros) and the Oriental Flower Beetle (Protaetia orientalis) have been studied during tethered flight with synchronized microphone array measurements and high speed video (1000–10,000 fps). The larger Coconut Rhinoceros Beetles have fundamental ∼50 Hz with distinctive torsional wing rotation compared to Oriental Flower Beetle (∼100 Hz). Computational fluid dynamics simulations were performed using the unsteady compressible flow solver (CAESIM, Adaptive Research, Inc.) using a highresolution (TVD) methodology. Models of the wing flapping motion were accomplished using mesh deformation techniques with the flapping following from rotation with prescribed bending and coupled rotation and translation from the wing’s hinge position. Fluid structure interactions with respect to the wing’s flexibility are investigated in terms of the wing bending and the leading edge vortex formation.

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4

Seshadri, Muralidhar, Jonathan B. Freund, Pranab N. Jha, Atchyuta Ramayya Venna, Darren Walters, and Srinivasan Jagannathan. "Improved Aero/Hydro Flow-Rate Model Using Acoustics." Petrophysics – The SPWLA Journal of Formation Evaluation and Reservoir Description 59, no. 4 (August 2018): 429–38. http://dx.doi.org/10.30632/pjv59v4-2018a1.

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5

ICHIKAWA, Nariyoshi, and Ye Li. "Aero Acoustics Simulation on the geometry of vehicle." Proceedings of Conference of Hokuriku-Shinetsu Branch 2003.40 (2003): 103–4. http://dx.doi.org/10.1299/jsmehs.2003.40.103.

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6

Hashem, I., M. H. Mohamed, and A. A. Hafiz. "Aero-acoustics noise assessment for Wind-Lens turbine." Energy 118 (January 2017): 345–68. http://dx.doi.org/10.1016/j.energy.2016.12.049.

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7

Zheng, Zheng Yu, and Ren Xian Li. "Analysis of the Automobile’s External Aerodynamic Noise Field Characteristics Based on CAA." Applied Mechanics and Materials 130-134 (October 2011): 58–62. http://dx.doi.org/10.4028/www.scientific.net/amm.130-134.58.

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This paper dwelled on the principle of Computational Aero-Acoustics (CAA), and utilized the Boundary Element Method (BEM) combined with the Computational Fluid Dynamics (CFD) based on Lighthill’s analogy to the automobile flow model, and converted the fluctuating flow pressure near the vehicle’s surface into the dipole source boundary condition in acoustics grid, and eventually succeeded in simulating the external aerodynamic noise field of automobile by introducing the dipole source boundary condition into the automobile’s BEM model. The distribution of vehicle’s external aero-acoustics field and the directivity of vehicle’s surface aerodynamic acoustic dipole source were also discussed carefully in this paper. The results show that: The head and tail of car are the main aerodynamic noise source radiation areas, and most of the dipole source’s SPL value is more than 70dB; the variation in car speed greatly impacts on the directivity of aerodynamic noise field near the car’s tail surface (θ=165°~195°).

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8

KALTENBACHER, MANFRED. "COMPUTATIONAL ACOUSTICS IN MULTI-FIELD PROBLEMS." Journal of Computational Acoustics 19, no. 01 (March 2011): 27–62. http://dx.doi.org/10.1142/s0218396x11004286.

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We present physical/mathematical models base on partial differential equations (PDEs) and efficient numerical simulation schemes based on the Finite Element (FE) method for multi-field problems, where the acoustic field is the field of main interest. Acoustics, the theory of sound, is an emerging scientific field including disciplines from physics over engineering to medical science. We concentrate on the following three topics: vibro-acoustics, aero-acoustics and high intensity focused ultrasound. For each topic, we discuss the physical/mathematical modeling, efficient numerical schemes and provide practical applications.

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9

Yang, Dang Guo, Yong Hang Wu, Jin Min Liang, and Jun Liu. "An Investigation on Numerical Simulation Method for Aero-Acoustics Based on Acoustics Analogy." Applied Mechanics and Materials 444-445 (October 2013): 462–67. http://dx.doi.org/10.4028/www.scientific.net/amm.444-445.462.

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A numerical simulation method on noise prediction, which incorporates aerodynamics and sound wave equations based on acoustic analogy, is presented in the paper. Near-field unsteady aerodynamic characteristic can be obtain by large eddy simulation (LES), and far-field propagation of sound waves and spatial sound-field can be obtain by solving the time-domain integral equations of Ffowcs Williams and Hawings (FW-H). Based on the method, a numerical simulation was done on a two-dimension cylinder and a three-dimension flat plate with blunt leading edge. The agreement of numerical results with experiment data validated the Feasibility of the method. The results also indicate that LES can describe vortex generation and shedding in the flow-fields, and FW-H formulation, which has taken time-lag between sound emission and reception times into account, can simulate time-effect of sound propagation toward far-fields.

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10

Karim, Ahsanul, Meisam Mehravaran, Brian Lizotte, Keith Miazgowicz, and Yi Zhang. "Computational Aero-Acoustics Simulation of Automotive Radiator Fan Noise." SAE International Journal of Engines 8, no. 4 (April 14, 2015): 1743–49. http://dx.doi.org/10.4271/2015-01-1657.

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11

Gabard, G., R. J. Astley, P. Gamallo, and G. Kennedy. "Reprint of: Physics-Based Computational Methods for Aero-Acoustics." Procedia IUTAM 1 (2010): 183–92. http://dx.doi.org/10.1016/j.piutam.2010.10.020.

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12

Astley, R. J., and G. Gabard. "Computational Aero-Acoustics (CAA) for Aircraft Noise Prediction—Part A." Journal of Sound and Vibration 330, no. 16 (August 2011): 3785–86. http://dx.doi.org/10.1016/j.jsv.2011.05.004.

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13

Astley, R. J., and G. Gabard. "Computational Aero-Acoustics (CAA) for Aircraft Noise Prediction—Part B." Journal of Sound and Vibration 330, no. 17 (August 2011): 4081–82. http://dx.doi.org/10.1016/j.jsv.2011.05.005.

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14

Calvo, M., J. M. Franco, J. I. Montijano, and L. Rández. "Highly stable RK time advancing schemes for Computational Aero Acoustics." SeMA Journal 50, no. 1 (March 2010): 83–98. http://dx.doi.org/10.1007/bf03322543.

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15

Mohamed, M. H. "Aero-acoustics noise evaluation of H-rotor Darrieus wind turbines." Energy 65 (February 2014): 596–604. http://dx.doi.org/10.1016/j.energy.2013.11.031.

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16

Murad, Nurul, Jamal Naser, Firoz Alam, and Simon Watkins. "Computational fluid dynamics study of vehicle A-pillar aero-acoustics." Applied Acoustics 74, no. 6 (June 2013): 882–96. http://dx.doi.org/10.1016/j.apacoust.2012.12.011.

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17

Si, Hai Qing, Bing Wang, Yan Shi, and Xiao Jun Wu. "Aero-Acoustics Computations of Square Cylinder Using the Lattice Boltzmann Method." Applied Mechanics and Materials 444-445 (October 2013): 400–405. http://dx.doi.org/10.4028/www.scientific.net/amm.444-445.400.

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In this paper the ability of the Lattice Boltzmann Method (LBM) is investigated for simulating acoustic problems, especially for the propagation of acoustic waves in a wall bounded region. To treat the wall boundary conditions, a non-equilibrium extrapolation scheme for the LBM is adopted. LBM is next applied to simulate the complex aerodynamic noise generated from a square cylinder. In order to efficiently suppress the disturbances at the computational boundaries, the improved absorbing boundary condition (IABC) is developed in this paper. To validate the flow and acoustic solution of a square cylinder, comparisons between the present LBM and the previous studies are carried out. It is demonstrated that the LBM can efficiently simulate the noise generated from a square cylinder.

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18

Kim, J. S., H. S. Kim, and K. T. Hyun. "DEVELOPMENT OF UNEVEN FAN BY AERO-ACOUSTICS ANALYSIS & OPTIMIZATION METHOD." Journal of computational fluids engineering 17, no. 1 (March 31, 2012): 16–22. http://dx.doi.org/10.6112/kscfe.2012.17.1.016.

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19

Lacor, Chris. "HIGH-ORDER ACCURATE SCHEMES AND LES WITH APPLICATIONS IN AERO-ACOUSTICS." International Conference on Applied Mechanics and Mechanical Engineering 15, no. 15 (May 1, 2012): 1. http://dx.doi.org/10.21608/amme.2012.37000.

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20

Sutliff, Daniel L., and Bruce E. Walker. "Artificial noise systems for parametric studies of turbo-machinery aero-acoustics." International Journal of Aeroacoustics 15, no. 1-2 (March 2016): 103–30. http://dx.doi.org/10.1177/1475472x16630851.

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21

Drabek, Pavel, and Martin Zalesak. "CAA Approaches for Duct Elements of HVAC Systems." MATEC Web of Conferences 328 (2020): 01015. http://dx.doi.org/10.1051/matecconf/202032801015.

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In recent years there has been a significant increase in computing performance. This has allowed companies to make more use of numerical simulation methods during the development phase, even for areas that until recently were almost unfeasible. This article presents the fundamental aspects related to Computational Aero-Acoustics for internal flow with a focus on HVAC elements. The aim was to answer questions about the computational mesh, computational models and boundary conditions.

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22

Yang, Dang-Guo, Bo Lu, Jin-Sheng Cai, Jun-Qiang Wu, Kun Qu, and Jun Liu. "Investigation on flow oscillation modes and aero-acoustics generation mechanism in cavity." Modern Physics Letters B 32, no. 12n13 (May 10, 2018): 1840046. http://dx.doi.org/10.1142/s0217984918400468.

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Unsteady flow and multi-scale vortex transformation inside a cavity of L/D = 6 (ratio of length to depth) at Ma = 0.9 and 1.5 were studied using the numerical simulation method of modified delayed detached eddy simulation (DDES) in this paper. Aero-acoustic characteristics for the cavity at same flow conditions were obtained by the numerical method and 0.6 m by 0.6 m transonic and supersonic wind-tunnel experiments. The analysis on the computational and experimental results indicates that some vortex generates from flow separation in shear-layer over the cavity, and the vortex moves from forward to downward of the cavity at some velocity, and impingement of the vortex and the rear-wall of the cavity occurs. Some sound waves spread abroad to the cavity fore-wall, which induces some new vortex generation, and the vortex sheds, moves and impinges on the cavity rear-wall. New sound waves occur. The research results indicate that sound wave feedback created by the impingement of the shedding-vortices and rear cavity face leads to flow oscillations and noise generation inside the cavity. Analysis on aero-acoustic characteristics inside the cavity is feasible. The simulated self-sustained flow-oscillation modes and peak sound pressure on typical frequencies inside the cavity agree well with Rossiter’s and Heller’s predicated results. Moreover, the peak sound pressure occurs in the first and second flow-oscillation modes and most of sound energy focuses on the low-frequency region. Compared with subsonic speed (Ma = 0.9), aerodynamic noise is more intense at Ma = 1.5, which is induced by compression wave or shock wave in near region of fore and rear cavity face.

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23

Xu, L., and J. D. Denton. "Aero-acoustics of modern transonic fans — Fan noise reduction from its sources." Journal of Thermal Science 12, no. 2 (May 2003): 104–13. http://dx.doi.org/10.1007/s11630-003-0050-8.

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24

Li, Yanbing, and Xiaowen Shan. "Lattice Boltzmann method for adiabatic acoustics." Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences 369, no. 1944 (June 13, 2011): 2371–80. http://dx.doi.org/10.1098/rsta.2011.0109.

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The lattice Boltzmann method (LBM) has been proved to be a useful tool in many areas of computational fluid dynamics, including computational aero-acoustics (CAA). However, for historical reasons, its applications in CAA have been largely restricted to simulations of isothermal (Newtonian) sound waves. As the recent kinetic theory-based reformulation establishes a theoretical framework in which LBM can be extended to recover the full Navier–Stokes–Fourier (NS) equations and beyond, in this paper, we show that, at least at the low-frequency limit (sound frequency much less than molecular collision frequency), adiabatic sound waves can be accurately simulated by the LBM provided that the lattice and the distribution function ensure adequate recovery of the full NS equations.

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25

Kim, Joo-Hyung, Jin-Hyuk Kim, Seungyeol Shin, Kwang-Yong Kim, and Seungbae Lee. "Three-Dimensional Noise Analysis of an Axial-Flow Fan using Computational Aero-Acoustics." KSFM Journal of Fluid Machinery 15, no. 5 (October 1, 2012): 48–53. http://dx.doi.org/10.5293/kfma.2012.15.5.048.

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26

Song, Ji-Hun, and Dong-Ryul Lee. "A Study on Aero-Acoustics of High-Speed Turbomachinery for Different Rotational Speeds." Journal of the Korean Society for Precision Engineering 37, no. 12 (December 1, 2020): 897–904. http://dx.doi.org/10.7736/jkspe.020.072.

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27

AONO, Hikaru, Wataru OBAYASHI, Tomoaki TATSUKAWA, Kozo FUJII, Naoya MURAKAMI, Koichi TAKEDA, and Kazutoshi TAKEMI. "A Study of Aero-acoustics and Unsteady Flow Dynamics of Rotating Small Fan." Proceedings of the Fluids engineering conference 2019 (2019): OS5–09. http://dx.doi.org/10.1299/jsmefed.2019.os5-09.

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28

TSUTAHARA, Michihisa. "F091002 Direct Simulation of Aero-acoustics by the Finite-Difference Lattice Boltzmann Method." Proceedings of Mechanical Engineering Congress, Japan 2014 (2014): _F091002–1—_F091002–4. http://dx.doi.org/10.1299/jsmemecj.2014._f091002-1.

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29

van der Torn, Marein, Hans F. Mahieu, and Joost M. Festen. "Aero-acoustics of silicone rubber lip reeds for alternative voice production in laryngectomees." Journal of the Acoustical Society of America 110, no. 5 (November 2001): 2548–59. http://dx.doi.org/10.1121/1.1398053.

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30

Tsutahara, Michihisa. "The finite-difference lattice Boltzmann method and its application in computational aero-acoustics." Fluid Dynamics Research 44, no. 4 (April 19, 2012): 045507. http://dx.doi.org/10.1088/0169-5983/44/4/045507.

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31

Wu, Peng, and Johan Meyers. "Globally conservative high-order filters for large-eddy simulation and computational aero-acoustics." Computers & Fluids 48, no. 1 (September 2011): 150–62. http://dx.doi.org/10.1016/j.compfluid.2011.04.004.

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32

Kirkup. "The Boundary Element Method in Acoustics: A Survey." Applied Sciences 9, no. 8 (April 19, 2019): 1642. http://dx.doi.org/10.3390/app9081642.

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The boundary element method (BEM) in the context of acoustics or Helmholtz problems is reviewed in this paper. The basis of the BEM is initially developed for Laplace’s equation. The boundary integral equation formulations for the standard interior and exterior acoustic problems are stated and the boundary element methods are derived through collocation. It is shown how interior modal analysis can be carried out via the boundary element method. Further extensions in the BEM in acoustics are also reviewed, including half-space problems and modelling the acoustic field surrounding thin screens. Current research in linking the boundary element method to other methods in order to solve coupled vibro-acoustic and aero-acoustic problems and methods for solving inverse problems via the BEM are surveyed. Applications of the BEM in each area of acoustics are referenced. The computational complexity of the problem is considered and methods for improving its general efficiency are reviewed. The significant maintenance issues of the standard exterior acoustic solution are considered, in particular the weighting parameter in combined formulations such as Burton and Miller’s equation. The commonality of the integral operators across formulations and hence the potential for development of a software library approach is emphasised.

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33

Pierucci, Mauro. "Aero‐ and Hydro‐Acoustics edited by G. Comte‐Bellot and J. E. Ffowcs‐Williams." Journal of the Acoustical Society of America 82, no. 5 (November 1987): 1854. http://dx.doi.org/10.1121/1.395771.

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34

Murad, Nurul M., Jamal Naser, Firoz Alam, and Simon Watkins. "A computational fluid dynamics study of crosswind effects on vehicle A-pillar aero-acoustics." International Journal of Vehicle Noise and Vibration 9, no. 3/4 (2013): 147. http://dx.doi.org/10.1504/ijvnv.2013.055820.

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35

Van Hirtum, A., R. Blandin, and X. Pelorson. "A setup to study aero-acoustics for finite length ducts with time-varying shape." Applied Acoustics 105 (April 2016): 83–92. http://dx.doi.org/10.1016/j.apacoust.2015.11.019.

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36

Pei, Xi, Min Xu, and Dong Guo. "Aeroelastic-Acoustics Numerical Simulation Research." Applied Mechanics and Materials 226-228 (November 2012): 500–504. http://dx.doi.org/10.4028/www.scientific.net/amm.226-228.500.

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The generation of aerodynamic noise of aircraft in flight is due to dynamical system and aerodynamic .The response of aircraft subjected to High acoustic loads and aerodynamic loads can produce fatigue and damage. In this paper a new Aeroelastic- Acoustics which adds acoustic loads in aeroelastic is presented. The emphasis of the study is the discipline of displacement and load of the flexible structure under the unsteady aerodynamic, inertial, elastic and aero-acoustic. The CFD/CSD/CAA coupling is used to simulate rockets cabin. Sound generated by a rocker is predicted numerically from a Large Eddy simulation (LES) of unsteady flow field. The Lighthill acoustic analogy is used to model the propagation of sound. The structural response of rocket cabin was given. The boundary-layer transition on the pressure side of the cabin is visualized, by plotting to better illustrate the essential interaction between fluctuating pressure and structure.CFD/CSD/CAA coupling compute method is validated in low and middle frequency.

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37

Koukounian, Viken. "Developing and validating analytical tools to predict the aero-acoustic performance of bespoke noise mitigation solutions." Journal of the Acoustical Society of America 155, no. 3_Supplement (March 1, 2024): A284. http://dx.doi.org/10.1121/10.0027518.

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The characterization of empirical knowledge from observations is, generally, referred to as the Scientific Method. Most engineering best practices rely on ‘observations’ (e.g., laboratory testing) to make informed decisions for future projects and/or applications. While this approach is still considered to be the ‘state of the art’ in most fields of acoustics, it is especially relevant in the studies of architectural acoustics and environmental noise. Since it is not possible to test every permutation of product (and/or its configurations) and environmental conditions, the results of only common geometries and parameters are reported in databases for use by professionals. However, the described framework is rigid and prohibits true optimization of a solution which should consider the solution’s performance requirements, as well as the various constraints (site, project, multi-physics). A more sophisticated approach is possible, where analytical tools are developed to predict the multi-physics performance of products (such as silencers, plenum-silencers, louvers and enclosures). Numerical methods are relied on to validate these new tools against empirical data. The presented work demonstrates the optimization of a product’s aero-acoustic performance according to multi-variable constraints.

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38

Wu, Weimin, Wenling Dong, Shiwei Li, and Suocheng Zhang. "Aero-acoustics Investigation of a Bionic Airfoil Horizontal Axis Wind Turbine Using LES-DCS Approach." Journal of Physics: Conference Series 2280, no. 1 (June 1, 2022): 012001. http://dx.doi.org/10.1088/1742-6596/2280/1/012001.

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Abstract The wind turbine noise has become an important issue in the current green energy field, therefore, it is necessary to use new and advantageous methods to study the problem. This research employed the LBM-DCS method to investigate the wake sound radiation characteristics for a bionic airfoil horizontal axis wind turbine, combining the large eddy simulation (LES) model and the wall-adapting local eddy-viscity (WALE) model. The obtained results show that the aeroacoustic model used here is reasonable and effective, which are consistent with the relevant experimental measurement result. The appearance and changing characteristics of the acoustic radiation ring have been discussed and analyzed to a certain extent. Based on the accumulation of this research, we will combine more experimental data to carry out a further systematic investigation on the acoustic radiation characteristics to the wind turbine.

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39

Semiletov, V. A., and S. A. Karabasov. "Cabaret Scheme for Computational Aero Acoustics: Extension to Asynchronous Time Stepping and 3D Flow Modelling." International Journal of Aeroacoustics 13, no. 3-4 (June 2014): 321–36. http://dx.doi.org/10.1260/1475-472x.13.3-4.321.

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40

Mahdal, Miroslav, Josef Dobeš, and Milada Kozubková. "Measurement of Aerodynamic and Acoustic Quantities Describing Flow around a Body Placed in a Wind Tunnel." Measurement Science Review 19, no. 1 (February 1, 2019): 20–28. http://dx.doi.org/10.2478/msr-2019-0004.

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Abstract Aerodynamically generated noise affects passenger comfort in cars, high-speed trains, and airplanes, and thus, automobile manufacturers aim for its reduction. Investigation methods of noise and vibration sources can be divided into two groups, i.e. experimental research and mathematical research. Recently, owing to the increase in computing power, research in aerodynamically generated noise (aero-acoustics) is beginning to use modern methods such as computational fluid dynamics or fluid-structure interaction. The mathematical model of turbulent flow is given by the system of partial differential equations, its solution is ambiguous and thus requires verification by physical experiment. The results of numerical methods are affected by the boundary conditions of high quality gained from the actual experiment. This article describes an application of complex measurement methodology in the aerodynamic and acoustic (vibro-acoustic) fields. The first part of the paper is focused on the specification of the experimental equipment, i.e. the wind tunnel, which was significantly upgraded in order to obtain the relevant aerodynamics and vibro-acoustics data. The paper presents specific results from the measurement of the aerodynamic and vibro-acoustic fields.

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41

Innocenti, Alessandro, Antonio Andreini, Bruno Facchini, and Antonio Peschiulli. "Numerical analysis of the dynamic flame response of a spray flame for aero-engine applications." International Journal of Spray and Combustion Dynamics 9, no. 4 (May 16, 2017): 310–29. http://dx.doi.org/10.1177/1756827717703577.

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Incoming standards on NO x emissions are motivating many aero-engine manufacturers to adopt the lean burn combustion concept. One of the most critical issues affecting this kind of technology is the occurrence of thermo-acoustic instabilities that may compromise combustor life and integrity. Therefore the prediction of the thermo-acoustic behaviour of the system becomes of primary importance. In this paper, the complex interaction between the system acoustics and a turbulent spray flame for aero-engine applications is numerically studied. The dynamic flame response is computed exploiting reactive URANS simulations and system identification techniques. Great attention has been devoted to the impact of liquid fuel evolution and droplet dynamics. For this purpose, the GE Avio PERM (partially evaporating and rapid mixing) lean injection system has been analysed, focussing attention on the effect of several modelling parameters on the combustion and on the predicted flame response. A frequency analysis has also been set up and exploited to obtain even more insight on the dynamic flame response of the spray flame. The application is one of the few in the literature where the dynamic flame response of spray flames is numerically investigated, providing a description in terms of flame transfer function and detailed information on the physical phenomena.

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42

Guérin, Sébastien, Tobias Lade, Leandro Castelucci, and Ismaeel Zaman. "Broadband noise emission by a low-Mach low-Reynolds number propeller ingesting a boundary layer." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 268, no. 1 (November 30, 2023): 7038–49. http://dx.doi.org/10.3397/in_2023_1053.

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The broadband noise radiated by a low-speed two-bladed propeller immersed in a planar turbulent boundary layer (BL) is predicted by using an analytical approach developed in the past in response to a similar aero-acoustic problem. The experimental results come from two independent facilities having analogous characteristics. Excess broadband noise is assumed to be generated by the BL turbulence hitting the propeller blades. The aero-acoustic model is based on the acoustic analogy. It accounts for the fact that vortices can be chopped several times by the blades as they pass through the propeller. The "cigar" shape of the turbulence near the wall surface is considered in the turbulence model. If possible, the input parameters are retrieved from the hot-wire measurements carried out in the boundary layer, otherwise they are modelled. The propeller performance is calculated using BEMT. The effect of the flat plate on aerodynamics and acoustics is ignored. The results obtained with this heuristic approach are satisfactory in the orthogonal plane but the levels are underestimated by more than 10 dB in the downstream region of the horizontal plane. This suggests that a major effect is not captured by the current models. Measurements and predictions agree upon the fact that blade-to-blade correlations are not prominent for this configuration.

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43

Zhu, M., A. Tabbal, M. Megahed, G. Pierrot, and P. Ravier. "A Weak Compressible Flow Solution for Fluid and Air-Borne Acoustics Coupled Problems in a Nonlinear System." NAFEMS International Journal of CFD Case Studies 7 (August 2008): 47–56. http://dx.doi.org/10.59972/pt108tyk.

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This paper presents the implementation and validation of a numerical simulation method that takes into account the air-borne acoustic wave propagation within the turbulent flow solution at low Mach numbers. The method is called weak compressibility, and is used in order to cope with fully coupled aero-acoustics problem in a nonlinear system. The weak compressibility was implemented into an explicit incompressible flow solver using an edgebased finite element method. A single 3D cavity case was used to validate the method in comparison with the experiment. The simulated results showed good agreement with the experimental data with regards to the acoustic pressure and frequency for the dominant peak of the sound pressure level (SPL) spectra over a wide speed range from 15 to 55 meters per second.

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Emelyanov, Vladislav, Aleksey Tsvetkov, and Konstantin Volkov. "MECHANISMS OF GENERATION AND SOURCES OF NOISE IN SUPERSONIC JETS." Akustika 32 (March 1, 2019): 144–50. http://dx.doi.org/10.36336/akustika201932144.

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Interest in the development of models and methods focused on the mechanisms of noise generation in jet flows is due to strict noise requirements produced by various industrial devices, as well as the possibilities of using sound in engineering and technological processes. The tools of physical and computational modeling of gas dynamics and aero-acoustics problems are considered, and noise sources and mechanisms of noise generation in supersonic jet flows are discussed. The physical pattern of the flow in free supersonic under-expanded jets is discussed on the basis of experimental and numerical data, as well as the flow structure arising from the interaction of a supersonic under-expanded jet with a cylindrical cavity. The influence of the nozzle pressure ratio and cavity depth on the sound pressure level, amplitude and frequency characteristics of the flow parameters is studied.

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Liu, Min, Jia Bing Wang, and Ke-Qi Wu. "The Direct Aero-Acoustics Simulation of Flow around a Square Cylinder Using the CE/SE Scheme." Journal of Algorithms & Computational Technology 1, no. 4 (December 2007): 525–38. http://dx.doi.org/10.1260/174830107783133905.

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Noël, Jean-Yves, Mark Farall, and Luca Casarsa. "Aero-acoustics in a tangential blower: validation of the CFD flow distribution using advanced PIV techniques." International Journal of Multiphysics 1, no. 4 (December 2007): 377–92. http://dx.doi.org/10.1260/175095407783419325.

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Grace, Sheryl M., and Allan D. Pierce. "Nonlinear interactions of acoustic, vorticity, and entropy modes, with applications to computational aero‐ and hydro‐acoustics." Journal of the Acoustical Society of America 101, no. 5 (May 1997): 3080. http://dx.doi.org/10.1121/1.418786.

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Tsutsumi, Seiji, Shinichi Maruyama, Wataru Sarae, Keita Terashima, Tetsuo Hiraiwa, and Tatsuya Ishii. "Development of aero-vibro acoustics methods for predicting acoustic environment inside payload fairing at lift-off." Journal of the Acoustical Society of America 140, no. 4 (October 2016): 3096. http://dx.doi.org/10.1121/1.4969654.

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Ghasemian, Masoud, and Amir Nejat. "Aero-acoustics prediction of a vertical axis wind turbine using Large Eddy Simulation and acoustic analogy." Energy 88 (August 2015): 711–17. http://dx.doi.org/10.1016/j.energy.2015.05.098.

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Shiva Prasad Uppu and Naren Shankar Radha Krishnan. "Turbulent Airflows over Serrated Wings: A Review on Experimental and Numerical Analysis." Journal of Advanced Research in Fluid Mechanics and Thermal Sciences 109, no. 1 (October 16, 2023): 27–40. http://dx.doi.org/10.37934/arfmts.109.1.2740.

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The serrations on the blade's cutting edge and trailing edge are supposed to assist humans deal with noise, but the main idea is for research and use in nature. This research examines trailing edge extension hydrodynamics. Further, reducing the turbulent wake intensity behind the TE increases aerodynamic performance while leaving the static pressure distribution (as averaged across the span) substantially unaffected. Computational Aero-Acoustics simulates aerodynamic and acoustic reactions. This work discusses the experimental and computer simulations of turbulent flows. This paper provides the research to the technical community in the energy field (often non-specialists of turbulent flow investigations) with a summary of experimental and numerical techniques for investigating flows over a serrated wing, with a focus on the airfoil's self-noise generation mechanism and its main fields of application. The reader can use the given bibliography to determine the best method for the case of interest. This purpose means the individual tactics aren't discussed further. Given the breadth of acoustics, the experimental and numerical methods in this study can be used to forecast noise across serrated wings. It verifies that both strategies are still necessary, performing unique but complementary tasks.

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