Relevant bibliographies by topics / Visualization of Noise

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

Academic literature on the topic 'Visualization of Noise'

Author: Grafiati
Published: 4 June 2025
Last updated: 23 June 2025

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Journal articles on the topic "Visualization of Noise"

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Licitra, Gaetano, Matteo Bolognese, Claudia Chiari, Stefano Carpita, and Luca Fredianelli. "Noise Source Predominance Map: a new representation for strategic noise maps." Noise Mapping 9, no. 1 (2022): 269–79. http://dx.doi.org/10.1515/noise-2022-0163.

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Abstract Environmental noise prevention starts from strategic noise maps of main transport infrastructures and agglomerations. Graduated colors are representative of the average noise levels produced in space by each individual source, or the by the overall sum. Among their purposes, communication of results to population has been the most neglected. The present paper proposes predominance maps for the first time in environmental acoustic (NSP). NSP are visualization tool showing the predominant source in each point by means of polygons and colors. Also Intensity Noise Source Predominance maps (I-NSP) are proposed, which add visualizations of noise exposure levels to NSP by coloring the polygons according to a color-scale. Both NSP and I-NSP are new visualization that would help understanding and assigning responsibilities for exceeding limits, but they also represent a valid support for locating the acoustic monitoring stations when required. As case studies, the maps are calculated in port areas, as they are large areas with a great variability of different types of noise sources and represent a smaller case than agglomeration, but with higher complexity.
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Wickramathilaka, Nevil, Uznir Ujang, Suhaibah Azri, and Tan Liat Choon. "Calculation of Road Traffic Noise, Development of Data, and Spatial Interpolations for Traffic Noise Visualization in Three-dimensional Space." Geomatics and Environmental Engineering 17, no. 5 (2023): 61–85. http://dx.doi.org/10.7494/geom.2023.17.5.61.

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Road traffic noise visualization is vital in three-dimensional (3D) space. Designing noise observation points (NOPs) and the developments of spatial interpolations are key elements for the visualization of traffic noise in 3D. Moreover, calculating road traffic noise levels by means of a standard noise model is vital. This study elaborates on the developments of data and spatial interpolations in 3D noise visualization. In 3D spatial interpolation, the value is interpolated in both horizontal and vertical directions. Eliminating flat triangles is vital in the vertical direction. Inverse distance weighted (IDW), kriging, and triangular irregular network (TIN) are widely used to interpolate noise levels. Because these interpolations directly support the interpolation of three parameters, the developments of spatial interpolations should be applied to interpolate noise levels in 3D. The TIN noise contours are primed to visualize traffic noise levels while IDW and kriging provide irregular contours. Further, this study has identified that the TIN noise contours fit exactly with NOPs in 3D. Moreover, advanced kriging interpolation such as empirical Bayesian kriging (EBK) also provides irregular shape contours and this study develops a comparison for such contours. The 3D kriging in EBK provides a significant approach to interpolate noise in 3D. The 3D kriging voxels show a higher accurate visualization than TIN noise contours.
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Xiao-Xia Guo, Xiao-Xia Guo, Rui-Qi Zhang Xiao-Xia Guo, Shu-Hao Liu Rui-Qi Zhang, Chen Wan Shu-Hao Liu, Zhen-Yu Wang Chen Wan, and Rong-Rong Han Zhen-Yu Wang. "Visualization of Rotating Machinery Noise Based on Near Field Acoustic Holography." 電腦學刊 33, no. 4 (2022): 215–23. http://dx.doi.org/10.53106/199115992022083304018.

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<p>In order to solve the problem of fast identification of the noise source of rotating machinery, the time-space complex envelope model of monopole sound source is studied, and a modulation method of the complex envelope is proposed. A method combining near-field acoustic holography technology and complex envelope information is proposed to reconstruct the sound field and realize the identification of rotating machinery noise sources. Using the overall fluctuation of the signal to identify the noise source of the rotating machinery greatly reduces the amount of calculation, and speeds up the positioning speed while ensuring the positioning accuracy. According to the sound field radiation characteristics of rotating machinery noise, different measurement distances, different sampling points numbers and different reconstruction distances are selected to reconstruct the sound field. The simulation data analysis results show that the near-field acoustic holography technology can still obtain high sound field reconstruction accuracy under the condition of large reconstruction distance, and does not require high sampling points numbers. Using the envelope information extracted by envelope modulation technology to reconstruct the sound field can accurately identify the number and geometric distribution of sound sources. This technology not only speeds up data processing, but also ensures the accuracy of sound field reconstruction.</p> <p> </p>
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Pan, Jianping, Yuzhe He, Wei Ma, et al. "Machine Learning-Enhanced 3D GIS Urban Noise Mapping with Multi-Modal Factors." ISPRS International Journal of Geo-Information 14, no. 6 (2025): 223. https://doi.org/10.3390/ijgi14060223.

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Geographic Information System (GIS)-based noise management is crucial in urban environments as it provides precise spatial analysis, helping to identify noise hotspots and optimize noise control measures. By integrating noise propagation models with GIS technology, dynamic simulation and visualization of noise distribution can be achieved, offering scientific support for urban planning and noise management. Most existing noise prediction models fail to fully account for three-dimensional (3D) spatial information and a wide range of environmental factors. As a result, there are often discrepancies between the actual noise measurements at monitoring points and the predicted values generated by these models. Furthermore, there is a lack of a system that can effectively integrate noise data with three-dimensional scenes for simulation. This paper proposes a new method to simulate urban noise propagation, aiming to achieve more accurate noise prediction and visualization in a three-dimensional environment. First, we computed the preliminary noise propagation based on a traffic noise model. Next, machine learning techniques were applied to analyze the relationship between noise discrepancies and multi-modal factors, thereby improving the accuracy of environmental noise level estimation. Based on this, we developed an urban noise simulation system. The system integrates functions such as noise simulation, traffic simulation, and weather changes, enabling accurate noise visualization within a three-dimensional virtual environment. Experimental results demonstrate that this method enhances the accuracy of urban noise prediction and visualization, providing users with a more comprehensive understanding of the spatial distribution of urban noise.
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Celi, Roberto. "Time-Frequency Visualization of Helicopter Noise." Journal of the American Helicopter Society 46, no. 4 (2001): 262–72. http://dx.doi.org/10.4050/jahs.46.262.

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Hirata, Takeshi. "Fundamentals Knowledge and Visualization of Noise." JAPAN TAPPI JOURNAL 75, no. 12 (2021): 1097–103. http://dx.doi.org/10.2524/jtappij.75.1097.

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Vugdelija, Nikola, Rainer Splechtna, Goran Todorović, Mirko Sužnjević, and Krešimir Matković. "Comparative visualization for noise simulation data." Electronic Imaging 35, no. 1 (2023): 401–1. http://dx.doi.org/10.2352/ei.2023.35.1.vda-401.

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Yan, Suqing, Xiaonan Luo, Xiyan Sun, Jianming Xiao, and Jingyue Jiang. "Indoor Acoustic Signals Enhanced Algorithm and Visualization Analysis." Computational Intelligence and Neuroscience 2021 (July 31, 2021): 1–13. http://dx.doi.org/10.1155/2021/7592064.

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A pure acoustic signal can be easy to realize signal analysis and feature extraction. However, the surrounding noises will affect the content of acoustic signals as well as auditory fatigue to the audience. Therefore, it is vital to overcome the problem of noises that affect the acoustic signal. An indoor acoustic signal enhanced method based on image source (IS) method, filtered-x least mean square (FxLMS) algorithm, and the combination of Delaunay triangulation and fuzzy c-means (FCM) clustering algorithm is proposed. In the first stage of the proposed system, the IS method was used to simulate indoor impulse response. Next, the FxLMS algorithm was used to reduce the acoustic signals with noise. Lastly, the quiet areas are optimized and visualized by combining the Delaunay triangulation and FCM clustering algorithm. The experimental analysis results on the proposed system show that better noise reduction can be achieved than the most widely used least mean square algorithm. Visualization was validated with an intuitive understanding of the indoor sound field distribution and the quiet areas.
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Belsak, Ales, and Jurij Prezelj. "Investigating Sound Sources of Faulty Gear Units." Key Engineering Materials 417-418 (October 2009): 337–40. http://dx.doi.org/10.4028/www.scientific.net/kem.417-418.337.

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In diagnostics, the condition of mechanical systems can be determined very reliably on the basis of noise. Noise source visualization is based on a number of different methods. These methods are primarily intended for a specific noise source in a specific acoustic environment. In this paper, a visualization method of complex noise sources, based on the use of acoustic camera, is dealt with. All types of different complex noise sources can be visualized, using a special acoustic algorithm. Also, various transient acoustical phenomena can be observed.
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Tagami, Kotaro, Satoshi Ogasawara, and Hirohito Funato. "Visualization of Noise Propagation in Grounding System." IEEJ Transactions on Industry Applications 127, no. 2 (2007): 131–38. http://dx.doi.org/10.1541/ieejias.127.131.

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Dissertations / Theses on the topic "Visualization of Noise"

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Sheng, Nan. "Prediction and 3D Visualization of Environmental Indicators: Noise and Air Pollution." Thesis, KTH, Geodesi och satellitpositionering, 2011. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-91351.

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Environmental problems such as noise and air pollution are increasingly catching people’s attention in recent years owing to the industrialization and urbanization all over the world. Therefore it is important to develop effective methods to present information on noise and air pollution to the public. One feasible approach is to carry out prediction based on traffic data and make noise and pollution maps. GIS is a powerful tool for prediction since its spatial analysis function could be used in analysis and calculation. In addition the available GIS platforms also provide visualization functions to display the analysis results in variety of forms, in both 2D and 3D. This thesis uses noise and air pollution as examples to study how to predict noise and pollution from traffic data and how to visualize the predicted pollution information in 3D with the help of the existing visualization technology. Therefore, the thesis has two objectives. The first objective is focused on prediction of noise and air pollution using existing prediction models based on vehicle speed and traffic volume data. The original spatial road network dataset with traffic information was integrated with GIS and analysis and calculations were carried out. Road Traffic Noise-Nordic Prediction Method is used for predicting traffic noise while ARTEMIS model and OSPM model are applied for traffic air pollution. All analysis and calculations were carried out on virtual receiver points generated on ground surface and over building facades at different heights. The second objective is focused on 3D visualization of the predicted traffic noise and air pollution in ArcScene, Google Earth as well as X3D respectively. In ArcScene the virtual receiver points were visualized in their actual position with different colors representing noise or air pollution level. Then KML files were created from the point shapefiles and imported into Google Earth to show the noise and air pollution level in the virtual city available in Google Earth. Finally one layer of point shapefile was selected as an example to give the 3D scene in X3D. The selected layer of points was first interpolated into a continuous surface and converted into contours. Three types of models were developed in this part. First is to visualize contours in 3D using both colors and heights to show the noise or air pollution levels. Next the interpolated surface was segmented into scattered cells displayed also in colors and heights both representing pollution intensity. The last one is using 3D bars to show noise or air pollution in colors and lengths. The prediction results shows that the either noise or air pollution in the north part of central Stockholm is much more serious than in south part and the most polluted area appear along the highways. In the same area the pollution levels vary in different heights. The 3D visualization in ArcScene and Google Earth could clearly present the differences. However, so far the visualization in X3D only gives 2D information in 3D, which means although the 3D scenes were created, the height only noise or air pollution on the specific height could be represented. The real 3D representing is still need to be studied.<br>VisuCity
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Rami, Andrea. "Displacement mapping in cinematic scientific visualization." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2021.

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The main purpose of this dissertation is to study the cinematic scientific visualization pipeline followed during the internship carried out at CINECA, showing in particular a rendering technique used: the displacement mapping. The final animation, called "A Sacred Forest", is part of the "Into the (Un)Known" project, a scientific communication project. The first part of this dissertation explains what is cinematic scientific visualization and shows its pipeline, then the displacement mapping is described and analyzed with some examples made in Blender. Finally, the “making of” for the Sacred Forest animation is described, showing how astrophysical data provided by a simulation of a magnetic field generated around a supermassive black hole are filtered, mapped and then rendered to obtain the final result.
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Florin, Ernst-Ludwig, Tobias F. Bartsch, and Martin Kochanczyk. "Seeing is believing: direct visualization of fluctuations in biopolymer networks with 3D thermal noise imaging." Diffusion fundamentals 20 (2013) 10, S. 1, 2013. https://ul.qucosa.de/id/qucosa%3A13531.

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Chatellier, Ludovic. "Modélisation et contrôle actif des instabilités aéroacoustiques en cavité sous écoulement affleurant." Phd thesis, Université de Poitiers, 2002. http://tel.archives-ouvertes.fr/tel-00003529.

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La thèse présente la modélisation, l'étude expérimentale et le contrôle actif des instabilités aéroacoustiques rencontrées en cavité sous écoulement turbulent à faible nombre de Mach. On propose une formulation problème de stabilité de l'interface fluide séparant deux écoulements uniformes de vitesse différente en integrant les effets acoustiques. Les modes d'instabilité de l'interface sont alors étudiés en fonction du nombre de Mach et de la configuration géométrique. Une maquette comportant une cavité de dimensions réglables est ensuite étudiée en soufflerie à l'aide de mesures de pression. Ces données valident en partie l'approche analytique adoptée. On conçoit alors un dispositif de contrôle des modes d'instabilité, appliqué en particulier dans le cas de leur couplage avec l'acoustique de la veine d'essais. Enfin, un système de vélocimétrie par images de particules synchronisé sur les modes d'oscillation permet de valider l'étude théorique et la stratégie de contrôle.
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Hammarqvist, Ulf. "Audio editing in the time-frequency domain using the Gabor Wavelet Transform." Thesis, Uppsala universitet, Centrum för bildanalys, 2011. http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-153634.

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Visualization, processing and editing of audio, directly on a time-frequency surface, is the scope of this thesis. More precisely the scalogram produced by a Gabor Wavelet transform is used, which is a powerful alternative to traditional techinques where the wave form is the main visual aid and editting is performed by parametric filters. Reconstruction properties, scalogram design and enhancements as well audio manipulation algorithms are investigated for this audio representation.The scalogram is designed to allow a flexible choice of time-frequency ratio, while maintaining high quality reconstruction. For this mean, the Loglet is used, which is observed to be the most suitable filter choice.  Re-assignmentare tested, and a novel weighting function using partial derivatives of phase is proposed.  An audio interpolation procedure is developed and shown to perform well in listening tests.The feasibility to use the transform coefficients directly for various purposes is investigated. It is concluded that Pitch shifts are hard to describe in the framework while noise thresh holding works well. A downsampling scheme is suggested that saves on operations and memory consumption as well as it speeds up real world implementations significantly. Finally, a Scalogram 'compression' procedure is developed, allowing the caching of an approximate scalogram.
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Lin, Jia-Hong, and 林家鴻. "Microphone Arrays: Noise Source Identification and Sound Field Visualization." Thesis, 2011. http://ndltd.ncl.edu.tw/handle/98216542994638075902.

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博士<br>國立交通大學<br>機械工程學系<br>99<br>Farfield and nearfield microphone arrays are proposed for noise source identification (NSI) and sound field visualization (SFV). In farfield array, arrays with sparse and random microphone deployment are known to be capable of delivering high quality far-field images without grating lobes. In the optimal deployment of microphone arrays, global optimization techniques including the simulated annealing (SA) algorithm and the intra-block Monte Carlo (IBMC) algorithm are exploited to find the optimal microphone positions efficiently. In direction of arrival (DOA) estimation, the planar wave sources are assumed to be spherical wave sources in this thesis. Farfield acoustic imaging algorithms including the delay and sum (DAS) algorithm, the time reversal (TR) algorithm, the single input multiple output equivalent source inverse filtering (SIMO-ESIF) algorithm, the Minimum variance distortionless response (MVDR) algorithm and the multiple signal classification (MUSIC) algorithm are employed to estimate DOA. Results show that the MUSIC algorithm can attain the highest resolution of localizing sound sources positions. In narfield array, a nearfield equivalence source imaging (NESI) technique is proposed to identify locations and strengths of noise sources. The NESI is based on the time-domain formulation that applies not only to stationary but also a transient noise. Multichannel inverse filters are designed using the least-square optimization. Regularization is employed to mitigate the ill-posedness inherent in the model-matching problem. Window design can also be incorporated into the inverse filters to overcome defocusing problems when the distance of reconstruction (DOR) is large or when the number of microphones is less than that of the focal points. As a basic form of the equivalent source method (ESM) applied to nearfield acoustical holography (NAH) problems, discrete monopoles are utilized to represent the sound field of interest. When setting up the virtual source distribution, it is vital to maintain a “retreat distance” (RD) between the virtual sources and the actual source surface such that reconstruction would not suffer from singularity problems. However, one cannot increase the distance without bound because of the ill-posedness inherent in the reconstruction process with large distance. How to reach the best compromise between the reconstruction errors induced by the point source singularity and the reconstruction ill-posedness is an interesting problem in its own right. This thesis revisits this issue, with the aid of an optimization algorithm based on the golden section search (GSS) and parabolic interpolation. The results revealed that the RD appropriate for the ESM ranged from 0.4 to 0.5 times the spacing for the planar piston, while from 0.8 to 1.7 times average spacing for the spherical piston. Acoustical variable including sound pressure, particle velocity, active intensity and sound power are calculated by using multichannel regularized inverse filters. In practical applications in which only patch array with scarce sensors are available, a virtual microphone approach is employed to ameliorate edge effects using extrapolation and to improve imaging resolution using interpolation. The multichannel inverse filters are implemented in light of a highly efficient state-space minimal realization technique. A special kind of beam pattern and cost function definition is used for the multiple-input-multiple-output (MIMO) imaging problem. A striking result was also obtained that random deployment presents no particular benefit in nearfield imaging and the optimal configuration is the uniform array. As indicated by the simulation and experiment results, the proposed technique proved effective in identifying sources of many kinds, including broadband, narrowband, stationary, and transient sources.
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Yu, Chang-lung, and 游昌隆. "Flow Visualization and Flow-Induced Noise of a Cross-Flow Fan." Thesis, 2001. http://ndltd.ncl.edu.tw/handle/25549163511331430313.

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Tu, Tsung-Hsien, and 涂聰賢. "An Experimental Investigation on Noise Reduction and Internal Flow Visualization of a Cross-Flow Fan with Rotor-Skew-AngleSkew-Angle." Thesis, 2009. http://ndltd.ncl.edu.tw/handle/zww2b3.

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博士<br>國立臺北科技大學<br>機電科技研究所<br>97<br>The rotor-skew-angle design was proposed in this research for lowering the cross-flow-fan emitted noise, especially for the significantly narrow band noise accompanying with the blade operation. Following 0, 5, and 10 degree of rotor-skew-angle designs, the cross-flow fan radiated noise and its sound quality were evaluated. The pressure fluctuations were measured at different positions along the axial direction on the tonge. The coherence analysis was utilized for illustrating the blade passing frequency cancellation mechanism. A 3-D flow visualization method, which overcame the blind slight from LDV and PTV, was used to present the differences of internal flow patterns. The experimental results indicated that RSA-5, which was a rotor with a nearly a pitch skewed within impeller’s two end shrouds, had a lower sound emission and little pressure drops relative to that of no skew-angle case, RSA-0. RSA-10, two pitches twisting case, also had a better acoustics quietness than that of RSA-0, but it exited undesired noise in high frequency components around 2 – 4 kHz (3rd and 4th harmonics of the blade passing frequency). In this research, for a compromise between flow and acoustics performance, RSA-5 showed the most suitable design for cross-flow fan rotor.
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Saravanan, S. "Experimental Investigation Of The Effect Of Nose Cavity On The Aerothermodynamics Of The Missile Shaped Bodies Flying At Hypersonic Mach Numbers." Thesis, 2007. https://etd.iisc.ac.in/handle/2005/694.

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Hypersonic vehicles are exposed to severe heating loads during their flight in the atmosphere. In order to minimize the heating problem, a variety of cooling techniques are presently available for hypersonic blunt bodies. Introduction of a forward-facing cavity in the nose tip of a blunt body configuration of hypersonic vehicle is one of the most simple and attractive methods of reducing the convective heating rates on such a vehicle. In addition to aerodynamic heating, the overall drag force experienced by vehicles flying at hypersonic speeds is predominate due to formation of strong shock waves in the flow. Hence, the effective management of heat transfer rate and aerodynamic drag is a primary element to the success of any hypersonic vehicle design. So, precise information on both aerodynamic forces and heat transfer rates are essential in deciding the performance of the vehicle. In order to address the issue of both forces and heat transfer rates, right kind of measurement techniques must be incorporated in the ground-based testing facilities for such type of body configurations. Impulse facilities are the only devices that can simulate high altitude flight conditions. Uncertainties in test flow conditions of impulse facilities are some of the critical issues that essentially affect the final experimental results. Hence, more reliable and carefully designed experimental techniques/methodologies are needed in impulse facilities for generating experimental data, especially at hypersonic Mach numbers. In view of the above, an experimental program has been initiated to develop novel techniques of measuring both the aerodynamic forces and surface heat transfer rates. In the present investigation, both aerodynamic forces and surface heat transfer rates are measured over the test models at hypersonic Mach numbers in IISc hypersonic shock tunnel HST-2, having an effective test time of 800 s. The aerodynamic coefficients are measured with a miniature type accelerometer based balance system where as platinum thin film sensors are used to measure the convective heat transfer rates over the surface of the test model. An internally mountable accelerometer based balance system (three and six-component) is used for the measurement of aerodynamic forces and moment coefficients acting on the different test models (i.e., blunt cone with after body, blunt cone with after body and frustum, blunt cone with after body-frustum-triangular fins and sharp cone with after body-frustum-triangular fins), flying at free stream Mach numbers of 5.75 and 8 in hypersonic shock tunnel. The main principle of this design is that the model along with the internally mounted accelerometer balance system are supported by rubber bushes and there-by ensuring unrestrained free floating conditions of the model in the test section during the flow duration. In order to get a better performance from the accelerometer balance system, the location of accelerometers plays a vital role during the initial design of the balance. Hence, axi-symmetric finite element modeling (FEM) of the integrated model-balance system for the missile shaped model has been carried out at 0° angle of attack in a flow Mach number of 8. The drag force of a model was determined using commercial package of MSC/NASTRAN and MSC/PATRAN. For test flow duration of 800 s, the neoprene type rubber with Young’s modulus of 3 MPa and material combinations (aluminum and stainless steel material used as the model and balance) were chosen. The simulated drag acceleration (finite element) from the drag accelerometer is compared with recorded acceleration-time history from the accelerometer during the shock tunnel testing. The agreement between the acceleration-time history from finite-element simulation and measured response from the accelerometer is very good within the test flow domain. In order to verify the performance of the balance, tests were carried out on similar standard AGARD model configurations (blunt cone with cylinder and blunt cone with cylinder-frustum) and the results indicated that the measured values match very well with the AGARD model data and theoretically estimated values. Modified Newtonian theory is used to calculate the aerodynamic force coefficient analytically for various angles of attack. Convective surface heat transfer rate measurements are carried out by using vacuum sputtered platinum thin film sensors deposited on ceramic substrate (Macor) inserts which in turn are embedded on the metallic missile shaped body. Investigations are carried out on a model with and without fin configurations in HST-2 at flow Mach number of 5.75 and 8 with a stagnation enthalpy of 2 MJ/kg for zero degree angle of attack. The measured heating rates for the missile shaped body (i.e., with fin configuration) are lower than the predicted stagnation heating rates (Fay-Riddell expression) and the maximum difference is about 8%. These differences may be due to the theoretical values of velocity gradient used in the empirical relation. The experimentally measured values are expressed in terms of normalized heat transfer rates, Stanton numbers and correlated Stanton numbers, compared with the numerically estimated results. From the results, it is inferred that the location of maximum heating occurs at stagnation point which corresponds to zero velocity gradient. The heat-transfer ratio (q1/Qo)remains same in the stagnation zone of the model when the Mach number is increased from 5.75 to 8. At the corners of the blunt cone, the heat transfer rate doesn’t increase (or) fluctuate and the effects are negligible at two different Mach numbers (5.75 and 8). On the basis of equivalent total enthalpy, the heat-transfer rate with fin configuration (i.e., at junction of cylinder and fins) is slightly higher than that of the missile model without fin. Attempts have also been made to evaluate the feasibility of using forward facing cavity as probable technique to reduce the heat transfer rate and to study its effect on aerodynamic coefficients on a 41° apex angle missile shaped body, in hypersonic shock tunnel at a free stream Mach number of 8. The forward-facing circular cavities with two different diameters of 6 and 12 mm are chosen for the present investigations. Experiments are carried out at zero degree angle of attack for heat transfer measurements. About 10-25 % reduction in heat transfer rates is observed with cavity at gauge locations close to stagnation region, whereas the reduction in surface heat transfer rate is between 10-15 % for all other gauge locations (which is slightly downstream of the cavity) compared with the model without cavity. In order to understand the influence of forward facing cavities on force coefficients, measurement of aerodynamic forces and moment coefficients are also carried out on a missile shaped body at angles of attack. The same six component balance is also being used for subsequent investigation of force measurement on a missile shaped body with forward facing cavity. Overall drag reductions of up to 5 % is obtained for a cavity of 6 mm diameter, where as, for the 12 mm cavity an increase in aerodynamic drag is observed (up to about 10%). The addition of cavity resulted in a slight increase in the missile L/D ratio and did not significantly affect the missile lateral components. In summary, the designed balances are found to be suitable for force measurements on different test models in flows of duration less than a millisecond. In order to compliment the experimental results, axi-symmetric, Navier-Stokes CFD computations for the above-defined models are carried out for various angles of attack using a commercial package CFX-Ansys 5.7. The experimental free stream conditions obtained from the shock tunnel are used for the boundary conditions in the CFD simulation. The fundamental aerodynamic coefficients and heat transfer rates of experimental results are shown to be in good agreement with the predicted CFD. In order to have a feeling of the shock structure over test models, flow visualization experiments have been carried out by using the Schlieren technique at flow Mach numbers of 5.75 and 8. The visualized shock wave pattern around the test model consists of a strong bow shock which is spherical in shape and symmetrical over the forebody of the cone. Experimentally measured shock stand-off distance compare well with the computed value as well as the theoretically estimated value using Van Dyke’s theory. These flow visualization experiments have given a factual proof to the quality of flow in the tunnel test section.
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10

Saravanan, S. "Experimental Investigation Of The Effect Of Nose Cavity On The Aerothermodynamics Of The Missile Shaped Bodies Flying At Hypersonic Mach Numbers." Thesis, 2007. http://hdl.handle.net/2005/694.

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Abstract:
Hypersonic vehicles are exposed to severe heating loads during their flight in the atmosphere. In order to minimize the heating problem, a variety of cooling techniques are presently available for hypersonic blunt bodies. Introduction of a forward-facing cavity in the nose tip of a blunt body configuration of hypersonic vehicle is one of the most simple and attractive methods of reducing the convective heating rates on such a vehicle. In addition to aerodynamic heating, the overall drag force experienced by vehicles flying at hypersonic speeds is predominate due to formation of strong shock waves in the flow. Hence, the effective management of heat transfer rate and aerodynamic drag is a primary element to the success of any hypersonic vehicle design. So, precise information on both aerodynamic forces and heat transfer rates are essential in deciding the performance of the vehicle. In order to address the issue of both forces and heat transfer rates, right kind of measurement techniques must be incorporated in the ground-based testing facilities for such type of body configurations. Impulse facilities are the only devices that can simulate high altitude flight conditions. Uncertainties in test flow conditions of impulse facilities are some of the critical issues that essentially affect the final experimental results. Hence, more reliable and carefully designed experimental techniques/methodologies are needed in impulse facilities for generating experimental data, especially at hypersonic Mach numbers. In view of the above, an experimental program has been initiated to develop novel techniques of measuring both the aerodynamic forces and surface heat transfer rates. In the present investigation, both aerodynamic forces and surface heat transfer rates are measured over the test models at hypersonic Mach numbers in IISc hypersonic shock tunnel HST-2, having an effective test time of 800 s. The aerodynamic coefficients are measured with a miniature type accelerometer based balance system where as platinum thin film sensors are used to measure the convective heat transfer rates over the surface of the test model. An internally mountable accelerometer based balance system (three and six-component) is used for the measurement of aerodynamic forces and moment coefficients acting on the different test models (i.e., blunt cone with after body, blunt cone with after body and frustum, blunt cone with after body-frustum-triangular fins and sharp cone with after body-frustum-triangular fins), flying at free stream Mach numbers of 5.75 and 8 in hypersonic shock tunnel. The main principle of this design is that the model along with the internally mounted accelerometer balance system are supported by rubber bushes and there-by ensuring unrestrained free floating conditions of the model in the test section during the flow duration. In order to get a better performance from the accelerometer balance system, the location of accelerometers plays a vital role during the initial design of the balance. Hence, axi-symmetric finite element modeling (FEM) of the integrated model-balance system for the missile shaped model has been carried out at 0° angle of attack in a flow Mach number of 8. The drag force of a model was determined using commercial package of MSC/NASTRAN and MSC/PATRAN. For test flow duration of 800 s, the neoprene type rubber with Young’s modulus of 3 MPa and material combinations (aluminum and stainless steel material used as the model and balance) were chosen. The simulated drag acceleration (finite element) from the drag accelerometer is compared with recorded acceleration-time history from the accelerometer during the shock tunnel testing. The agreement between the acceleration-time history from finite-element simulation and measured response from the accelerometer is very good within the test flow domain. In order to verify the performance of the balance, tests were carried out on similar standard AGARD model configurations (blunt cone with cylinder and blunt cone with cylinder-frustum) and the results indicated that the measured values match very well with the AGARD model data and theoretically estimated values. Modified Newtonian theory is used to calculate the aerodynamic force coefficient analytically for various angles of attack. Convective surface heat transfer rate measurements are carried out by using vacuum sputtered platinum thin film sensors deposited on ceramic substrate (Macor) inserts which in turn are embedded on the metallic missile shaped body. Investigations are carried out on a model with and without fin configurations in HST-2 at flow Mach number of 5.75 and 8 with a stagnation enthalpy of 2 MJ/kg for zero degree angle of attack. The measured heating rates for the missile shaped body (i.e., with fin configuration) are lower than the predicted stagnation heating rates (Fay-Riddell expression) and the maximum difference is about 8%. These differences may be due to the theoretical values of velocity gradient used in the empirical relation. The experimentally measured values are expressed in terms of normalized heat transfer rates, Stanton numbers and correlated Stanton numbers, compared with the numerically estimated results. From the results, it is inferred that the location of maximum heating occurs at stagnation point which corresponds to zero velocity gradient. The heat-transfer ratio (q1/Qo)remains same in the stagnation zone of the model when the Mach number is increased from 5.75 to 8. At the corners of the blunt cone, the heat transfer rate doesn’t increase (or) fluctuate and the effects are negligible at two different Mach numbers (5.75 and 8). On the basis of equivalent total enthalpy, the heat-transfer rate with fin configuration (i.e., at junction of cylinder and fins) is slightly higher than that of the missile model without fin. Attempts have also been made to evaluate the feasibility of using forward facing cavity as probable technique to reduce the heat transfer rate and to study its effect on aerodynamic coefficients on a 41° apex angle missile shaped body, in hypersonic shock tunnel at a free stream Mach number of 8. The forward-facing circular cavities with two different diameters of 6 and 12 mm are chosen for the present investigations. Experiments are carried out at zero degree angle of attack for heat transfer measurements. About 10-25 % reduction in heat transfer rates is observed with cavity at gauge locations close to stagnation region, whereas the reduction in surface heat transfer rate is between 10-15 % for all other gauge locations (which is slightly downstream of the cavity) compared with the model without cavity. In order to understand the influence of forward facing cavities on force coefficients, measurement of aerodynamic forces and moment coefficients are also carried out on a missile shaped body at angles of attack. The same six component balance is also being used for subsequent investigation of force measurement on a missile shaped body with forward facing cavity. Overall drag reductions of up to 5 % is obtained for a cavity of 6 mm diameter, where as, for the 12 mm cavity an increase in aerodynamic drag is observed (up to about 10%). The addition of cavity resulted in a slight increase in the missile L/D ratio and did not significantly affect the missile lateral components. In summary, the designed balances are found to be suitable for force measurements on different test models in flows of duration less than a millisecond. In order to compliment the experimental results, axi-symmetric, Navier-Stokes CFD computations for the above-defined models are carried out for various angles of attack using a commercial package CFX-Ansys 5.7. The experimental free stream conditions obtained from the shock tunnel are used for the boundary conditions in the CFD simulation. The fundamental aerodynamic coefficients and heat transfer rates of experimental results are shown to be in good agreement with the predicted CFD. In order to have a feeling of the shock structure over test models, flow visualization experiments have been carried out by using the Schlieren technique at flow Mach numbers of 5.75 and 8. The visualized shock wave pattern around the test model consists of a strong bow shock which is spherical in shape and symmetrical over the forebody of the cone. Experimentally measured shock stand-off distance compare well with the computed value as well as the theoretically estimated value using Van Dyke’s theory. These flow visualization experiments have given a factual proof to the quality of flow in the tunnel test section.
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Books on the topic "Visualization of Noise"

1

Lepicovsky, J. Coherent large-scale structures in high Reynolds number supersonic jets. Lockheed-Georgia Company, 1985.

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R, Laflin K., and United States. National Aeronautics and Space Administration., eds. Reynolds-averaged Navier-Stokes simulations of two partial-span flap wing experiments. American Institute of Aeronautics and Astronautics, 1998.

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R, Laflin K., and United States. National Aeronautics and Space Administration., eds. Reynolds-averaged Navier-Stokes simulations of two partial-span flap wing experiments. American Institute of Aeronautics and Astronautics, 1998.

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R, Laflin K., and United States. National Aeronautics and Space Administration., eds. Reynolds-averaged Navier-Stokes simulations of two partial-span flap wing experiments. American Institute of Aeronautics and Astronautics, 1998.

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Reynolds-averaged Navier-Stokes simulations of two partial-span flap wing experiments. American Institute of Aeronautics and Astronautics, 1998.

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Vernallis, Carol, Amy Herzog, and John Richardson, eds. The Oxford Handbook of Sound and Image in Digital Media. Oxford University Press, 2013. http://dx.doi.org/10.1093/oxfordhb/9780199757640.001.0001.

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This collection of essays explores the relations between sound and image in a rapidly shifting landscape of audiovisual media in the digital age. Featuring contributions from scholars who bring with them an impressive array of disciplinary expertise, from film studies and philosophy to musicology, pornography, digital gaming, and media studies, the book charts new territory by analyzing what it calls the “media swirl” and the “audiovisual turn.” It draws on a range of media texts including blockbuster cinema, video art, music videos, video games, amateur video compilations, visualization technologies, documentaries, and immersive theater to address myriad subjects such as the transition of cinematic discourses to digital production and distribution, the relations between screens and public space, and the shifting nature of noise within digital ecosystems. It also examines noise, droning, and silence as recurring themes in New Extremist films of Europe, along with temporal and generic anomalies by citing examples such as the Silent Hill videogame series, the performance/installation Sleep No More, and the poetics of David Lynch’s Inland Empire. In addition, the book discusses the translation of information into digital media, how music has both shaped and become embedded within the aesthetic culture of political conflict, the nature of “realism” in relation to new audiovisual media networks, and the accelerated aesthetics of networked mediascape and the ways in which they may be connected to contemporary labor and global capitalism.
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Book chapters on the topic "Visualization of Noise"

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Reichenbach, Andre, Mario Hlawitschka, Marc Tittgemeyer, and Gerik Scheuermann. "Choosing a Tractography Algorithm: On the Effects of Measurement Noise." In Mathematics and Visualization. Springer International Publishing, 2013. http://dx.doi.org/10.1007/978-3-319-02475-2_11.

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Hahn, Klaus R., Sergej Prigarin, Susanne Heim, and Khader Hasan. "Random Noise in Diffusion Tensor Imaging, its Destructive Impact and Some Corrections." In Mathematics and Visualization. Springer Berlin Heidelberg, 2006. http://dx.doi.org/10.1007/3-540-31272-2_6.

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Delouille, V., P. Chainais, and J. F. Hochedez. "Spatial and Temporal Noise in Solar EUV Observations." In Solar Image Analysis and Visualization. Springer New York, 2008. http://dx.doi.org/10.1007/978-0-387-98154-3_17.

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de Leeuw, Willem C., Frits H. Post, and Remko W. Vaatstra. "Visualization of Turbulent Flow by Spot Noise." In Eurographics. Springer Vienna, 1996. http://dx.doi.org/10.1007/978-3-7091-7488-3_29.

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Shaheryar, Muhammad, Jong Taek Lee, and Soon Ki Jung. "Selective Noise-Aided Machine Unlearning with Deep Feature Visualization." In Lecture Notes in Computer Science. Springer Nature Switzerland, 2025. https://doi.org/10.1007/978-3-031-77389-1_8.

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Ujang, Muhamad Uznir, Nurul Qahirah Dzulkefley, Suhaibah Azri, and Syahiirah Salleh. "Three-Dimensional (3D) Noise Pollution Visualization via 3D City Modelling." In Application of Remote Sensing and GIS in Natural Resources and Built Infrastructure Management. Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-031-14096-9_18.

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Niermann, Christian A. "Effects of Background Noise and Visual Training on 3D Audio." In Human Interface and the Management of Information. Interaction, Visualization, and Analytics. Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-92043-6_21.

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Herman, Lukáš, and Tomáš Řezník. "Web 3D Visualization of Noise Mapping for Extended INSPIRE Buildings Model." In IFIP Advances in Information and Communication Technology. Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-41151-9_39.

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Verdenik, Anton. "Analysis and Visualization of Aluminum Reduction Cell Noise Based on Wavelet Transform." In Light Metals 2016. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-48251-4_66.

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Lim, Sukhyun, Kang-hee Seo, and Byeong-Seok Shin. "A Noise-Insensitive Hierarchical Min-Max Octree for Visualization of Ultrasound Datasets." In Computational Intelligence and Security. Springer Berlin Heidelberg, 2005. http://dx.doi.org/10.1007/11596448_122.

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Conference papers on the topic "Visualization of Noise"

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Rusu, Adrian, Amalia Rusu, and Soyong Byun. "Noise Visualization for Animal Welfare Improvement." In 2024 28th International Conference Information Visualisation (IV). IEEE, 2024. http://dx.doi.org/10.1109/iv64223.2024.00021.

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Marteney, Steven J. "Simple visualization technique for multi-dimensional frequency domain noise components." In Infrared Imaging Systems: Design, Analysis, Modeling, and Testing XXXVI, edited by Gerald C. Holst and David P. Haefner. SPIE, 2025. https://doi.org/10.1117/12.3053512.

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M, Baskaran, Jeevabarathi S, Kamalesh B, and Kumar P. "Autoencoder Based Noise Cancellation for Real-Time Audio Enhancement." In 2025 International Conference on Visual Analytics and Data Visualization (ICVADV). IEEE, 2025. https://doi.org/10.1109/icvadv63329.2025.10960934.

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Snehalatha, G., Saiteja Chennoji, Sai Lohitha Yele, and Sindhu Sri Bakna. "Design of a Kickback Noise Reduction Technique for Dynamic Comparators based on XOR-NMOS Switches." In 2025 International Conference on Visual Analytics and Data Visualization (ICVADV). IEEE, 2025. https://doi.org/10.1109/icvadv63329.2025.10961748.

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Dang, Eddie, Hanpeng Jiang, Haoyu Wang, et al. "PCB noise visualization system." In 2018 IEEE Long Island Systems, Applications and Technology Conference (LISAT). IEEE, 2018. http://dx.doi.org/10.1109/lisat.2018.8378015.

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KIM, S.-M., HS KWON, S.-H. PARK, and Y.-H. KIM. "EXPERIMENTAL COMPARISONS OF SOUND VISUALIZATION METHODS FOR MOVING NOISE SOURCES." In Inter-Noise 1996. Institute of Acoustics, 2024. http://dx.doi.org/10.25144/19835.

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Schroeder, L. E. "Visualization of Truck Interior Noise." In International Truck & Bus Meeting & Exhibition. SAE International, 2001. http://dx.doi.org/10.4271/2001-01-2808.

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Moravec, Marek. "DYNAMIC NOISE VISUALIZATION METHODS FOR IDENTIFICATION OF NOISE SOURCES." In 14th SGEM GeoConference on ECOLOGY, ECONOMICS, EDUCATION AND LEGISLATION. Stef92 Technology, 2014. http://dx.doi.org/10.5593/sgem2014/b51/s20.029.

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Shi, Tongyang, Yangfan Liu, J. Stuart Bolton, Frank Eberhardt, and Warner Frazer. "Diesel Engine Noise Source Visualization with Wideband Acoustical Holography." In Noise and Vibration Conference and Exhibition. SAE International, 2017. http://dx.doi.org/10.4271/2017-01-1874.

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PARCHEN, RR, JC BRUGGEMAN, and R. APTROOT. "BURNER PULSATIONS IN CENTRAL HEATING BOILERS: NUMERICAL SIMULATION OF BURNER-BOILER INTERACTION AND VISUALIZATION OF COMBUSTION INSTABILITY." In Inter-Noise 1996. Institute of Acoustics, 2024. http://dx.doi.org/10.25144/19785.

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