Relevant bibliographies by topics / Open-jet wind tunnel

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

Academic literature on the topic 'Open-jet wind tunnel'

Author: Grafiati
Published: 4 June 2021
Last updated: 19 February 2022

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Journal articles on the topic "Open-jet wind tunnel"

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Cooper, Kevin R., Edzard Mercker, and Jürg Müller. "The necessity for boundary corrections in a standard practice for the open-jet wind tunnel testing of automobiles." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 231, no. 9 (April 26, 2017): 1245–73. http://dx.doi.org/10.1177/0954407017701287.

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This paper is intended to provide a summary of the necessary adjustments required for road-representative open-jet wind tunnel measurements on automobiles. The open-jet wind tunnel provides accurate measurements, but they are made in a finite-sized jet that differs from the unconfined open-road conditions. Furthermore, measurements on a given automobile made in different open-jet wind tunnels disagree with each other, and with measurements in closed-wall wind tunnels that were corrected for the influences of their solid boundaries. There appears to be reticence at some company levels to making ‘corrections’ to open-jet measurements. Perhaps non-specialist managers think that the need for a ‘correction’ means an erroneous measurement. It does not! Any high-quality wind tunnel measurement is accurate, but it needs to be ‘calibrated’ to on-road conditions through an appropriate set of procedures. Closed-wall wind tunnels measure higher drag coefficients, in comparison with those in an unconstrained on-road flow. Open-jet wind tunnels frequently measure a lower value. The closed-wall adjustments lower the drag coefficient to the unconstrained value. Open-jet adjustments should also adjust the drag coefficient to the same unconstrained value. This paper explores the range of effects from the finite jet and elucidates the effectiveness of a two-measurement correction procedure. It is shown that not every data point must be measured twice, only a small selected subset. Since approximately 20% of tunnel occupancy is in the fan-on condition, then the additional cost of correct accurate on-road-equivalent data is low.
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Du, Longhuan, Arganthaël Berson, and Robert G. Dominy. "Aerofoil behaviour at high angles of attack and at Reynolds numbers appropriate for small wind turbines." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 229, no. 11 (September 8, 2014): 2007–22. http://dx.doi.org/10.1177/0954406214550016.

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The aerodynamic characteristics of a NACA0018 aerofoil have been investigated experimentally for incidence angles ranging from [Formula: see text] to [Formula: see text] in closed-jet and open-jet wind tunnels with different blockage coefficients at Reynolds numbers from 60,000 to 140,000. The results provide a comprehensive data set for studying the performance of typical, small-scale Darrieus wind turbine blades which mainly operate at relatively low Reynolds number and experience extreme angles of attack, particularly during start-up. Measurements in both very high and very low blockage, open-jet wind tunnels capture a “second-stall” phenomenon at high angles of attack, but this behaviour is not observed in the closed-jet wind tunnel confirming the sensitivity of aerofoil performance at extreme incidence to wind tunnel configuration. Surface flow visualisation suggests that the “second-stall” occurs when the flow separation point near the leading edge of the aerofoil moves from the suction side to the pressure side which leads to a sudden change of wake structure. In the closed-jet wind tunnel, the tunnel walls constrain the wake and prevent the flow from switching from one regime to another. The measured data are also used to demonstrate that established wind tunnel blockage corrections break down under these extreme, post-stall angles of attack.
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Cheung, C. W., and G. J. Hancock. "Wind tunnel interference on unsteady two-dimensional aerofoil motions in low speed flows." Aeronautical Journal 92, no. 913 (March 1988): 115–21. http://dx.doi.org/10.1017/s0001924000022016.

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Summary The aerodynamic characteristics of two-dimensional transient aerofoil motions in low-speed flows in a wind tunnel with either closed wall or open (jet) walls, including the effect of a downstream closed wall diffuser, have been investigated. The mathematical formulation for the aerofoil and its unsteady wake is based on linear theory and is solved by a piecewise linear vorticity method; the wall boundaries are represented by distributions of sources. Numerical calculations have been made for various values of tunnel height to chord ratio. Interference effects on the rate of build up of lift to a steady state following a step change in incidence can be large, especially for open jet tunnels.
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Urbahs, Aleksandrs, Dmitrijs Titovs, Margarita Urbaha, Sergejs Luckinskis, and Andrejs Aleksandrovs. "Multipurpose Alpha Mechanism for the Open-jet Wind Tunnel." Transport and Aerospace Engineering 1 (May 8, 2014): 54. http://dx.doi.org/10.7250/tae.2014.010.

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Mikhailov, Yu S., and Yu G. Stepanov. "SIMULATION OF 2D FLOW AROUND OF AIRFOILS AT LOW-SPEED WIND TUNNEL WITH OPEN JET TEST-SECTION." Civil Aviation High TECHNOLOGIES 22, no. 1 (February 27, 2019): 51–62. http://dx.doi.org/10.26467/2079-0619-2019-22-1-51-62.

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At present, there is a great interest in the development of new airfoils for wind turbines and high-lift wings of unmanned aerial vehicles (UAV). The requirements for such airfoils differ from conventional aircraft airfoils, because of structural reasons and extreme operating conditions. So, wind turbine airfoils operate frequently under fully separated flow when stall is used for power regulation at high wind speeds. At the same time design of airfoils for wings UAV poses the problem of availability of high-lift at low Reynolds number. Modern airfoils are to a large extent developed from numerical methods. However, the complex flow conditions such as separation at high angles of attack, laminar separation bubbles and the transition from laminar to turbulent flow are difficult to predict accurately. Hence, testing of airfoils at a two-dimensional condition is an important phase in airfoil design. The development and validation of a 2D testing facility for investigation of single and multi-element airfoils in the wind tunnel Т-102 with open test section are considered in this article. T-102 is a continuous-operation, closed-layout wind tunnel with two reverse channels. The test section has an elliptical cross-section of 4 ×2,33 m and a length of 4 m. Two big flat panels of the L × H=3 ×3,9 m size installed upright on balance frame aligned with the free stream are used for simulating two-dimensional flow in the tunnel test section. The airfoil section in the layout of a rectangular wing is mounted horizontally between flat panels with minimum gaps to ensure 2D flow conditions. The aerodynamic forces and pitch moment acting on the model were measured by wind tunnel balance. To determine boundary corrections for a new test section of wind tunnel, the experimental investigation of three geometrically similar models has been executed. The use of boundary corrections has provided good correlation of the test data of airfoil NACA 6712 with the results obtained from the wind tunnel except for lift and drag coefficient values at high angles of attack.
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Wang, Yigng, Zhigng Yang, and Qilang Li. "Methods to control low frequency pulsation in open-jet wind tunnel." Applied Acoustics 73, no. 6-7 (June 2012): 666–72. http://dx.doi.org/10.1016/j.apacoust.2012.01.002.

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Underbrink, James R. "Pletharrays for aeroacoustic phased array applications." International Journal of Aeroacoustics 16, no. 4-5 (July 2017): 202–29. http://dx.doi.org/10.1177/1475472x17718884.

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“Pletharrays” are introduced, motivated, and presented for application to aeroacoustic phased array measurements. Pletharrays contain a plethora of arrays composed from a modest to high number of array elements to field a remarkably large number of high element count arrays for use in noise source imaging applications. Pletharrays that have been deployed for closed jet transonic wind tunnel, static engine ground, open jet wind tunnel, and flyover phased array tests are presented. Tremendous array element leverage to provide extensive measurement flexibility and fidelity are demonstrated.
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Al-Faruk, Abdullah, and Ahmad Sharifian. "Geometrical optimization of a swirling Savonius wind turbine using an open jet wind tunnel." Alexandria Engineering Journal 55, no. 3 (September 2016): 2055–64. http://dx.doi.org/10.1016/j.aej.2016.07.005.

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Funke, Stefan, Larisa Kim, and Henri Siller. "Acoustic Measurements of a Contra-Rotating Open Rotor in an Open Jet Wind-Tunnel." International Journal of Aeroacoustics 11, no. 2 (June 2012): 197–212. http://dx.doi.org/10.1260/1475-472x.11.2.197.

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Migliore, Paul, and Stefan Oerlemans. "Wind Tunnel Aeroacoustic Tests of Six Airfoils for Use on Small Wind Turbines*." Journal of Solar Energy Engineering 126, no. 4 (November 1, 2004): 974–85. http://dx.doi.org/10.1115/1.1790535.

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Aeroacoustic tests of seven airfoils were performed in an open jet anechoic wind tunnel. Six of the airfoils are candidates for use on small wind turbines operating at low Reynolds numbers. One airfoil was tested for comparison to benchmark data. Tests were conducted with and without boundary layer tripping. In some cases, a turbulence grid was placed upstream in the test section to investigate inflow turbulence noise. An array of 48 microphones was used to locate noise sources and separate airfoil noise from extraneous tunnel noise. Trailing-edge noise was dominant for all airfoils in clean tunnel flow. With the boundary layer untripped, several airfoils exhibited pure tones that disappeared after proper tripping was applied. In the presence of inflow turbulence, leading-edge noise was dominant for all airfoils.
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Dissertations / Theses on the topic "Open-jet wind tunnel"

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Tourn, Cremona Silvana Cecilia. "Characterization of a New Open Jet Wind Tunnel to Optimize and Test Vertical Axis Wind Turbines." Doctoral thesis, Universitat Rovira i Virgili, 2017. http://hdl.handle.net/10803/461079.

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Basat en el creixent interès en les tecnologies ambientals urbanes, l'estudi de turinas d'eix vertical de petita escala mostra desafiaments motivadors. En aquesta tesi, es presenten els criteris de disseny, les característiques i potencialitats d'un nou túnel de vent de secció de prova oberta. Té un àrea de sortida i la broquet del túnel de 1,5 x 1,5 m2, i es pot operar amb velocitats de sortida de 3 m / s a ​​17 m / s. La caracterització del flux s'ha dut a terme amb tubs pitot calibrats, anemòmetres de cassoletes i anemòmetres de fil calent. Es consideren dues configuracions diferents de l'àrea de prova, amb i sense sostre. Els mesuraments en el rang de velocitats de sortida disponibles mostren que la secció transversal, on les intensitats de velocitat i turbulència mostren un nivell acceptable d'uniformitat, té una àrea de 0,8 x 0,8 m2 i una dimensió de 2 m des de la sortida del broquet del túnel. En aquesta secció de treball, la intensitat màxima de la turbulència és del 4%. La caracterització detallada del flux realitzat indica que el túnel de vent es pot utilitzar per provar models a d'aerogeneradors de petita escala.
Basado en el creciente interés en las tecnologías ambientales urbanas, el estudio de turinas de eje vertical de pequeña escala muestra desafíos motivadores. En esta tesis, se presentan los criterios de diseño, las características y potencialidades de un nuevo túnel de viento de seccion de prueba abierta. Tiene un área de salida e la boquilla del túnel de 1,5 x 1,5 m2, y se puede operar con velocidades de salida de 3 m/s a 17 m/s. La caracterización del flujo se ha llevado a cabo con tubos pitot calibrados, anemómetros de cazoletas y anemómetros de hilo caliente. Se consideran dos configuraciones diferentes del área de prueba, con y sin techo. Las mediciones en el rango de velocidades de salida disponibles muestran que la sección transversal, donde las intensidades de velocidad y turbulencia muestran un nivel aceptable de uniformidad, tiene un área de 0,8 x 0,8 m2 y una dimensión de 2 m desde la salida de la boquilla del túnel. En esta sección de trabajo, la intensidad máxima de la turbulencia es del 4%. La caracterización detallada del flujo realizado indica que el túnel de viento se puede utilizar para probar modelos a de aerogeneradores de pequeña escala.
Based on the increasing interest in urban environmental technologies, the study of small scale vertical axis wind turbines shows motivating challenges. In this thesis, we present the design criteria, characteristics and potentials of a new open jet wind tunnel. It has a nozzle exit area of 1.5 x1.5 m2, and it can be operated with exit velocities from 3 m/s to 17 m/s. The characterization of the flow has been carried out with calibrated pitot tubes, cup anemometers, and hot wire anemometers. Two different configurations of the test area, with and without a ceiling, are considered. Measurements in the range of available exit velocities show that the cross section, where the velocity and turbulence intensities show an acceptable level of uniformity, has an area of 0.8 x 0.8 m2 and a streamwise dimension of 2 m from the nozzle exit of the tunnel. In this working section, the maximum turbulence intensity is 4%. The detailed characterization of the flow carried out indicates that the wind tunnel can be used to test small scale models of wind turbines.
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Owens, David Elliot. "Wall Features of Wing-Body Junctions: Towards Noise Reduction." Thesis, Virginia Tech, 2013. http://hdl.handle.net/10919/23717.

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Much research and experiments have gone into studying idealized wing-body junction flows and their impact on horseshoe vortex and wake formation.  The vortices have been found to generate regions of high surface pressure fluctuations and turbulence that are detrimental to structural components and acoustics.  With the focus in the military and commercial industry on reducing the acoustical impact of aircraft and their engines, very little research has been done to examine the potential impact wing-body junctions may have on acoustics, especially for high lifting bodies such as propellers.  Two similar tests were conducted in the Virginia Tech Open Jet Wind Tunnel where boundary layer measurements, oil flow visualizations, acoustic linear array and surface pressure fluctuation measurements of a baseline Rood airfoil model and two novel junction fairing designs were all taken.  Boundary layer measurements were taken at four locations along the front half of the flat plate and the profiles were shown to be all turbulent despite the low Reynolds number of the flow, (test 1: Re_"<1400, test 2: Re_"<550).  Oil flow visualizations were taken and compared to those of previous researchers and the location of separation and line of low shear along with the maximum width of the wake and width of wake at the trailing edge all scaled relatively well with the Momentum Deficit Factor, defined for wing-body junction flows [Fleming, J. L., Simpson, R. L., Cowling, J. E. & Devenport, W. J., 1993. An Experimental Study of a Turbulent Wing-Body Junction and Wake Flow. Experiments in Fluids, Volume 14, pp. 366-378. ].  A linear microphone array was used to estimate the directivity of the facility acoustic background noise to be used to improve background subtraction methods for surface pressure fluctuation measurements.  Surface pressure fluctuation spectra were taken ahead of the leading edge of the plate and along the surface of the models.  These showed that the fairings reduced pressure fluctuations along the plate upstream of the leading edge, with fairing 1 reducing them to clean tunnel flow levels.  On the surface of the models, the fairings tended to reduce low frequency (<1000Hz) pressure fluctuation peaks when compared to the baseline model and increase the pressure fluctuations in the high frequency range.  Simple scaling arguments indicate that this spectral change may be more beneficial than detrimental as low frequency acoustics especially those between 800 Hz and 1200 Hz are the frequencies that humans perceive as the loudest noise levels.  Scaling the frequencies measured to those of full scale applications using Strouhal numbers show that frequencies below 1000 Hz in this experiment result in frequencies at the upper limit of the human hearing frequency range.  Low frequency acoustic waves also tend to travel farther and high frequency acoustic waves are more apt to be absorbed by the surrounding atmosphere.
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Sholtis, Paul M. "Characterization of Upstream Effects Due to High Blockage in the AFRL Vertical Wind Tunnel." University of Dayton / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=dayton155594746187138.

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Milbank, Juliette, and milbank@turbulenflow com au. "Investigation of fluid-dynamic cavity oscillations and the effects of flow angle in an automotive context using an open-jet wind tunnel." RMIT University. Aerospace, Mechanical & Manufacturing Engineering, 2005. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20090723.121800.

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Aeroacoustic whistles are a significant source of customer complaints to automotive manufacturers. Whistles can occur on many such components, but the relative position and configuration of rearview mirrors means they are a more problematic source of tonal noise on vehicles. The low subsonic complex turbulent flow, combined with small cavity scales, determines the possible whistle mechanisms. The one considered to be most problematic, fluid-dynamic cavity resonance, is the topic of this research thesis. The research scope is limited to the automotive environment of external rearview mirrors and the fluid-dynamic resonance mechanism: low subsonic Mach number, M = 0.05 - 0.13; laminar boundary layers; and two-dimensional, acoustically compact cavities. The low unit-cost of rearview mirrors and the desire to have simple identification and prediction schemes, that could be used by production engineers, determined an empirical approach. A search of the existing literature revealed that there were some data on cavities of the above scale in low Mach number flow, but quoted errors in empirical descriptions were large and there was very little research on the effects of flow yaw angle on the chosen resonance mechanism. The research therefore aims to determine whether existing empirical descriptions of fluid-dynamic cavity resonance are suitable for the prediction of the resonance characteristics, with sufficient accuracy to enable unambiguous identification of the presence of the resonance and its mechanism. A second aim is to investigate the effects of a feature of the automotive flow environment, flow yaw angle, on the resonance. Flow yaw angle is determined by those components of the flow in the same plane as the surface in which the cavity is situated. An experimental program was undertaken using a purpose-built aeroacoustic wind tunnel and a simple cavity model. Testing with two types of cavity configurations, as well as flow visualisation, investigated the main features of the resonance in time-averaged yawed flow. Within the scope of this thesis, it is shown that fluid-dynamic cavity resonance characteristics can be accurately identified by a simple empirical model, even in yawed flow. Various descriptors allow identification of the resonance threshold, stage, frequency and relative amplitude in non-yawed flow, while the frequency and stage can also be identified in yawed flow. The relative decrease in resonance amplitude in yawed flow, although identified for these experiments, would depend on the degree of spanwise variation in the boundary layer characteristics for a given cavity configuration. The results also identify significant issues with testing in a free jet tunnel, due to the nature of fluid-dynamic cavity resonance and the fluctuation energy content in free shear layers. Despite this, the thesis aims are achieved, and appropriate design guidelines are produced for automotive designers.
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Bennaceur, Iannis. "Etude numérique de la diffusion d'une onde acoustique par une couche de cisaillement turbulente à l'aide d'une simulation aux grandes échelles." Thesis, Aix-Marseille, 2017. http://www.theses.fr/2017AIXM0187/document.

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Lors des mesures acoustiques dans les souffleries à veine ouverte, les ondes acoustiques émises par une maquette ou une source située dans la veine se propagent dans la couche de cisaillement turbulente qui se forme aux abords du jet avant d’être reçues par les microphones localisés en dehors. L’onde acoustique interagit avec le champ de vitesse turbulent de la couche de mélange ce qui a pour effet de modifier son contenu spectral, de redistribuer spatialement son énergie et de moduler sa phase et son amplitude, on parle alors de diffusion acoustique. Cette thèse a consisté à l’étude de la diffusion d’une onde acoustique par une couche de cisaillement turbulente à l’aide d’une simulation numérique aux grandes échelles. Pour cela, il a d’abord été nécessaire de réaliser la simulation numérique aux grandes échelles d’une couche de cisaillement turbulente plane dans son régime auto-similaire. Dans un second temps, nous avons simulé l’interaction entre une onde acoustique et l’écoulement turbulent afin d’étudier les caractéristiques du champ de pression diffusé qui en résulte. Nous avons notamment vérifié que la simulation était capable de prédire précisément les fréquences sur lesquelles est répartie la plupart de l’énergie acoustique ainsi que la forme du spectre de pression diffusé. Finalement, le champ de vitesse du milieu turbulent qui est corrélé avec l’enveloppe du champ de pression diffusé a été reconstruit à l’aide de la méthode de l’estimation stochastique linéaire. Cette méthode nous a notamment permis de visualiser les larges structures turbulentes qui interviennent principalement dans le mécanisme de diffusion acoustique
During open jet wind tunnel measurements, the acoustic waves emitted by a device or an acoustic source located inside the flow propagate inside the turbulent shear layer that develops at the periphery of the jet before being received by microphones located outside the flow. The acoustic wave interacts with the turbulent velocity field leading to a change of directivity, a phase and amplitude modulation as well as a spectral re-distribution of the acoustic energy over a band of frequencies. This phenomenon is known as acoustic scattering. This work has consisted in the study of the scattering of an acoustic wave by a turbulent shear layer using large-eddy simulation. The first step of the study has consisted in the large-eddy simulation of a turbulent shear layer in its self-similar state. In a second second step, the direct computation of the interaction between the acoustic wave and the turbulent flow has been performed in order to study the characteristics of the resulting scattered pressure field. It has been shown that the numerical simulation is able to accurately predict the frequencies on which the main part of the scattered energy is redistributed, as well as the shape of the scattered pressure spectrum. Finally, the turbulent velocity field which is correlated with the envelope of the scattered pressure field is reconstructed using the linear stochastic estimation method. This method has enabled the visualization of the large turbulent structures that mainly take part in the acoustic scattering mechanism
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Collin, Christopher [Verfasser], Thomas [Akademischer Betreuer] Indinger, Thomas [Gutachter] Indinger, and Jochen [Gutachter] Wiedemann. "Interference Effects in Automotive, Open Jet Wind Tunnels / Christopher Collin ; Gutachter: Thomas Indinger, Jochen Wiedemann ; Betreuer: Thomas Indinger." München : Universitätsbibliothek der TU München, 2019. http://d-nb.info/1200547543/34.

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Shao-DongLyu and 呂紹棟. "Measurements of Multi-Blade Wind Turbine Wakes in an Open-Jet Wind Tunnel." Thesis, 2017. http://ndltd.ncl.edu.tw/handle/avvg5v.

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碩士
國立成功大學
工程科學系
105
In this study, the wake characteristics of two-blade, three-blade, and four-blade wind turbines were investigated experimentally. The experiments were carried out in an open-jet wind tunnel under a uniform incoming flow condition. Hot-wire and Cobra-probe anemometers were used to measure the mean and fluctuating quantities of turbulent flows at different locations with downwind distance. The blade element momentum (BEM) theory is used to model the streamwise velocity distribution in the near wake region and the results from the BEM theory were compared with the measurements by using a hot-wire anemometer. We carried out the wake measurements with turbines in two conditions: (a) in different yaw angles (0° and 30°) by using hot-wire anemometer, and (b) in non-yaw condition by different anemometers (hot-wire and Cobra probe). The measurement results indicate that: (a) The yawed turbines wake have an obvious shifting phenomena and the ‘wake-region width‘ as well as wake characteristics are smaller than normal turbines; (b) The hot-wire and Cobra-probe anemometers are consistent with turbulent characteristics except the vertical velocity. The power spectrum analysis demonstrates that the turbulence dissipation rate from both anemometers measurements follows as the slope of -5/3 in the inertial subrange. The reliability of the data can be confirmed by the consistency with the first harmonic peak in the spectra plots and rotating speed from the laser tachometer.
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Hsin-YunChang and 張馨云. "Comparison of Experimental Measurements and Numerical Simulations for Vertical Axis Wind Turbine Wakes in an Open-Jet Wind Tunnel." Thesis, 2018. http://ndltd.ncl.edu.tw/handle/58z89p.

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碩士
國立成功大學
工程科學系
106
Energy made human life progress, and science technology advanced faces an issue which the energy consumption increased. Using the renewable energy is a method for solving the problem of energy scarcity, the wind power generation has more interest in the countries around the world. The wind turbines are according to their structures divided into vertical axis wind turbine (VAWT) and horizontal axis wind turbine (HAWT). The HAWT has commonly applied in open space and that the high efficiency at high wind speed. However, the VAWT has unlimited potential in power generation which the advantage is not a lot of restrictions on the site and the flow direction. The research relevant the VAWT is mostly about the analysis and comparison of its performance characteristics. The wake characteristics are also important for wind energy development. In this study, comparison of experimental measurements and numerical simulations for vertical axis wind turbine wakes in an open-jet wind tunnel which the wind turbine model is an airfoil NACA9412 four-blade VAWT. The two kinds of experimental measuring instruments in the experiment which are the cobra probe and the hot wire probe for comparing the result between different measurement instruments. In the CFD simulation part, the transient Navier-Stokes equations are solved using the Large Eddy Simulation (LES). We use the SIMPLE algorithm in the split solver and the coupled algorithm in the coupled solver for solve and compare the wake characteristics. The results were analyzed normalized time-averaged velocity of streamwise and spanwise, the turbulence intensity for streamwise and spanwise, and momentum flux at the horizontal plane. The spectrum analysis with data collected using the cobra probe and the hot-wire probe shows the expected slope of -5/3 to indicate the inertial subrange, which increases the reliability of the data measured in this experiment. In order to develop the wind energy and accurate VAWT models that though the VAWT wake compaction of the measuring experiment and the CFD simulation.
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Books on the topic "Open-jet wind tunnel"

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Manuel, Gregory S. Effect of collector configuration on test section turbulence levels in an open-jet wind tunnel. Hampton, Va: Langley Research Center, 1992.

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Fischer, Oliver. Investigation of Correction Methods for Interference Effects in Open-Jet Wind Tunnels. Wiesbaden: Springer Fachmedien Wiesbaden, 2018. http://dx.doi.org/10.1007/978-3-658-21379-4.

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Effect of collector configuration on test section turbulence levels in an open-jet wind tunnel. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

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1956-, Martin R. M., and Ames Research Center, eds. Background noise measurements from jet exit vanes designed to reduce flow pulsations in an open-jet wind tunnel. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1985.

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Aerodynamic testing of road vehicles in open jet wind tunnels. Warrendale, PA: Society of Automotive Engineers, 1999.

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Fischer, Oliver. Investigation of Correction Methods for Interference Effects in Open-Jet Wind Tunnels. Springer Vieweg, 2018.

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Aerodynamic Testing of Road Vehicles in Open Jet Wind Tunnels (S P (Society of Automotive Engineers)). Society of Automotive Engineers Inc, 1999.

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Book chapters on the topic "Open-jet wind tunnel"

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Fischer, Oliver. "Wind Tunnel Interference Effects." In Investigation of Correction Methods for Interference Effects in Open-Jet Wind Tunnels, 19–24. Wiesbaden: Springer Fachmedien Wiesbaden, 2018. http://dx.doi.org/10.1007/978-3-658-21379-4_3.

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Fischer, Oliver. "Correction Method for Interference Effects in Open-Jet Wind Tunnels." In Investigation of Correction Methods for Interference Effects in Open-Jet Wind Tunnels, 25–40. Wiesbaden: Springer Fachmedien Wiesbaden, 2018. http://dx.doi.org/10.1007/978-3-658-21379-4_4.

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Fischer, Oliver. "Introduction." In Investigation of Correction Methods for Interference Effects in Open-Jet Wind Tunnels, 1–4. Wiesbaden: Springer Fachmedien Wiesbaden, 2018. http://dx.doi.org/10.1007/978-3-658-21379-4_1.

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Fischer, Oliver. "Aerodynamic Development Tools." In Investigation of Correction Methods for Interference Effects in Open-Jet Wind Tunnels, 5–17. Wiesbaden: Springer Fachmedien Wiesbaden, 2018. http://dx.doi.org/10.1007/978-3-658-21379-4_2.

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Fischer, Oliver. "Computational Fluid Dynamics Investigations." In Investigation of Correction Methods for Interference Effects in Open-Jet Wind Tunnels, 41–86. Wiesbaden: Springer Fachmedien Wiesbaden, 2018. http://dx.doi.org/10.1007/978-3-658-21379-4_5.

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Fischer, Oliver. "Application and Investigation of the Correction Method." In Investigation of Correction Methods for Interference Effects in Open-Jet Wind Tunnels, 87–103. Wiesbaden: Springer Fachmedien Wiesbaden, 2018. http://dx.doi.org/10.1007/978-3-658-21379-4_6.

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Fischer, Oliver. "Comparison of Results." In Investigation of Correction Methods for Interference Effects in Open-Jet Wind Tunnels, 105–8. Wiesbaden: Springer Fachmedien Wiesbaden, 2018. http://dx.doi.org/10.1007/978-3-658-21379-4_7.

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Conference papers on the topic "Open-jet wind tunnel"

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Cook, Thomas, Sidaard Gunasekaran, Michael V. Ol, and Michael P. Mongin. "Frequency Response of a Shuttered Open Jet Wind Tunnel." In AIAA Scitech 2020 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-1760.

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Schoenleber, Christoph, Felix Wittmeier, and Jochen Wiedemann. "Influence of Open-Jet Effects on Vehicle Wind Tunnel Measurements." In Automotive Technical Papers. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2021. http://dx.doi.org/10.4271/2021-01-5014.

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Wickern, Gerhard. "A Theoretical Approach towards the Self-Correcting Open Jet Wind Tunnel." In SAE 2014 World Congress & Exhibition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2014. http://dx.doi.org/10.4271/2014-01-0579.

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Sims-Williams, D. B., and R. G. Dominy. "The Design of an Open-Jet Wind Tunnel for Model Testing." In Motorsports Engineering Conference & Exhibition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2002. http://dx.doi.org/10.4271/2002-01-3340.

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Newton, James M., Matthew P. Cameron, Raul Urbina, Richard W. Kimball, Andrew J. Goupee, and Krish P. Thiagarajan. "Characterization of a Wind Tunnel for Use in Offshore Wind Turbine Development." In ASME 2015 34th International Conference on Ocean, Offshore and Arctic Engineering. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/omae2015-41979.

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In this work a wind tunnel with an open jet configuration is investigated for use in offshore wind turbine testing. This study characterizes the open-jet wind-tunnel using measurements of the velocity field detailing mean velocities and turbulence intensities with and without a scaled wind turbine. Measurements have been taken downstream to evaluate the expected area of turbine operation and the shear zone. The effects on the flow due to the wake and turbine blockage have also been identified. Additionally, the combination of honeycomb and screens necessary to produce a homogeneous flow at the desired velocity with low turbulence intensity has been identified. This work provides a useful data set that will be used as a benchmark to evaluate the benefits of recirculating wind tunnels. The data set has resulted in identifying conditions that would prevent producing the desired flows. The data set has also resulted in recommendations concerning the shape of the wind tunnel sections at the University of Maine’s wind-wave (W2) facility to minimize its interactions with the turbine wake expansion, turbine blockage, and the turbine associated wake shear zone.
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Sheikh-AlShabab, Ahmed A., and Paul G. Tucker. "Numerical Investigation of Installation Effects in Open Jet Wind Tunnel Airfoil Experiments." In 52nd Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-1118.

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Rennie, Mark, Moo-Sang Kim, Jung-Ho Lee, and Jung-Do Kee. "Suppression of Open-Jet Pressure Fluctuations in the Hyundai Aeroacoustic Wind Tunnel." In SAE 2004 World Congress & Exhibition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2004. http://dx.doi.org/10.4271/2004-01-0803.

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Lacey, John. "A Study of the Pulsations in a 3/4 Open Jet Wind Tunnel." In SAE 2002 World Congress & Exhibition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2002. http://dx.doi.org/10.4271/2002-01-0251.

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Moreau, S., D. Neal, and J. Foss. "Hot Wire Measurements Around a CD Airfoil in an Open-Jet Anechoic Wind Tunnel." In ASME 2004 Heat Transfer/Fluids Engineering Summer Conference. ASMEDC, 2004. http://dx.doi.org/10.1115/ht-fed2004-56833.

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The aeroacoustic measurements in the ECL large anechoic wind tunnel, which originally focused on the wall pressure distribution and the far field acoustic pressure are extended to velocity measurements by hot-wire probes in the nozzle jet and in the vicinity of the subject airfoil. The present work focuses on the exit plane of the wind tunnel nozzle upstream of the test airfoil and in the LES computational domain that is embedded in the potential core around the airfoil mock-up at mid span. The inlet measurements by a single hot-wire probe provide some insight on free-stream turbulence intensity upstream of the profile. The X-array measurements on the upper and lower LES boundaries show the overall deflection of the jet potential core by the cambered airfoil. These are compared to the Fluent RANS predictions. The X-array measurements in the airfoil wake provide information on the development of the airfoil boundary layer and the resulting wake after separation. The measured wake velocity defect has been compared with both the RANS and LES predictions.
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Fischer, Oliver, Timo Kuthada, Jochen Wiedemann, Patrick Dethioux, Richa Mann, and Brad Duncan. "CFD Validation Study for a Sedan Scale Model in an Open Jet Wind Tunnel." In SAE World Congress & Exhibition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2008. http://dx.doi.org/10.4271/2008-01-0325.

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