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Dissertations / Theses on the topic 'Wind tunnels Flow visualization'

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Published: 4 June 2021

Last updated: 2 February 2022

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1

Hickle, Curtis. "Wind Tunnel renovation, flow verification and flapping wing analysis." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2006. http://library.nps.navy.mil/uhtbin/hyperion/06Jun%5FHickle.pdf.

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Thesis (M.S. in Mechanical Engineering)--Naval Postgraduate School, June 2006.<br>Thesis Advisor(s):Dr. Kevin Jones and Dr. Garth Hobson. "June 2006." Includes bibliographical references (p.79-81). Also available in print.

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2

Jones, Gregory Stephen. "The measurement of wind tunnel flow quality at transonic speeds." Diss., Virginia Tech, 1991. http://hdl.handle.net/10919/39109.

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The measurement of wind tunnel flow quality for the transonic flow regime has been plagued by the inability to interpret complex unsteady flow field information obtained in the free stream. Traditionally hot wire anemometry and fluctuating pressure techniques have been used to quantify the unsteady characteristics of a wind tunnel. This research focuses on the application of these devices to the transonic flow regime. Utilizing hot wire anemometry, one can decompose the unsteady flow field with a three sensor technique, to obtain fluctuations associated with the velocity, density, and total t

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3

Sumantran, V. "The effect of free stream disturbances and control surface deflections on the performance of the Wortmann airfoil at low Reynolds numbers." Diss., Virginia Polytechnic Institute and State University, 1985. http://hdl.handle.net/10919/49921.

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A wing with a Wortmann FX-63-137-ESM airfoil section has been used to study some unique problems encountered in wing aerodynamics in the range of Reynolds numbers between 50,000 and 500,000. The wind-tunnel testing conducted in the 6'x 6' Stability tunnel included strain-gauge data, pressure data, and flow-visualization studies. The laminar separation bubble which frequently occurs on the upper surface of the wing is found to dominate its performance and gives rise to a hysteresis loop for lift and drag. Changes in airfoil performance due to positive flap or control surface deflections resembl

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4

Sung, Bongzoo. "Analysis of the vortical flow around a 60 degree delta wing with vortex flap." Diss., Virginia Polytechnic Institute and State University, 1985. http://hdl.handle.net/10919/49932.

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Subsonic wind tunnel investigations were conducted on a 60° swept, flat plate, delta wing with a leading edge vortex flap. The pressure distributions were measured over a range of angles of attack starting from zero to 40° in 5° interval and flap deflection angles from zero to 45° with 5° increments at a Reynolds number of about 2.14 x 10‘ based on the root chord. The flow visualization experiments were performed from zero degree to the stall angle, with ten different flap deflection angles at the same Reynolds number. The mean flow field was measured at angles of attack l0° and 15° with the f

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5

Ringshia, Aditya K. "Aerodynamic Measurements in a Wind Tunnel on Scale Models of a 777 Main Landing Gear." Thesis, Virginia Tech, 2006. http://hdl.handle.net/10919/34583.

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Aerodynamic measurements were taken over models of the Boeing 777 high fidelity isolated landing gear in the 6- by 6-foot Virginia Tech Stability Wind Tunnel (VT-SWT) at a free-stream Mach number of 0.16. Noise control devices (NCD) were developed at Virginia Tech [9] to reduce noise by shielding gear components, reducing wake interactions and by streamlining the flow around certain landing gear components. Aerodynamic measurements were performed to understand the flow over the landing gear and also changes in the flow between "Baseline" and "NCD" configurations (without and with Noise Control

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6

Zakaria, Mohamed Yehia. "Unsteady Nonlinear Aerodynamic Modeling and Applications." Diss., Virginia Tech, 2016. http://hdl.handle.net/10919/79909.

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Unsteady aerodynamic modeling is indispensable in the design process of rotary air vehicles, flapping flight and agile unmanned aerial vehicles. Undesirable vibrations can cause high-frequency variations in motion variables whose effects cannot be well predicted using quasi-steady aerodynamics. Furthermore, one may exploit the lift enhancement that can be generated through an unsteady motion for optimum design of flapping vehicles. Additionally, undesirable phenomena like the flutter of fixed wings and ensuing limit cycle oscillations can be exploited for harvesting energy. In this dissertatio

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7

Clark, Kylen D. "A Numerical Comparison of Symmetric and Asymmetric Supersonic Wind Tunnels." University of Cincinnati / OhioLINK, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1447071393.

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8

Gordon, Robert. "Advanced 2-D and 3-D particle velocimetry techniques for quantitative fluid flow visualisation in real-time." Thesis, University of Aberdeen, 1997. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.262919.

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The aim of this study was to develop and implement a low cost, high speed, flow visualisation tool for 3-D velocity measurement throughout time dependent particle seeded fluid flow volumes. To achieve this, a new high performance wind / water tunnel was designed and constructed using CFD as a design aid. The tunnel provided the necessary platform for obtaining consistent high quality images of fluid flow. Images were grabbed using low cost CCD cameras and downloaded via a PC mounted image capture board, to system RAM. The conventional high cost laser sheet illumination method was replaced with

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9

Pannell, C. N. "Fibre-optic laser Doppler velocimetry." Thesis, University of Kent, 1988. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.383370.

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10

Jones, Michael Charles 1971. "A study of the mechanism for vortex breakdown and some measures for its control." Monash University, Dept. of Mechanical Engineering, 2002. http://arrow.monash.edu.au/hdl/1959.1/7694.

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11

Rosson, Joel Christopher. "Dynamic flow quality measurements in a transonic cryogenic wind tunnel." Thesis, Virginia Polytechnic Institute and State University, 1985. http://hdl.handle.net/10919/101463.

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Two instruments mounted in a piggyback arrangement were developed for time-resolved measurements of dynamic flow quality in a transonic cryogenic wind tunnel. The first one is a dual hot-wire aspirating probe for measurement of stagnation pressure and temperature. The second is a miniature high-frequency response angle probe consisting of surface mounted pressure sensors. The aspirating probe was tested in the 0.3-m Transonic Cryogenic Tunnel (TCT) at NASA-Langley Research Center. Stagnation pressure and temperature measurements were taken in the free-stream of the settling chamber and test

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12

El-Nahas, Waleed Mahmoud. "Effects of heating, breathing, hair style, posture, and air velocity on breathing zone concentrations for an anthropometrically-correct manikin in a wind tunnel." Morgantown, W. Va. : [West Virginia University Libraries], 2005. https://eidr.wvu.edu/etd/documentdata.eTD?documentid=4274.

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Thesis (Ph. D.)--West Virginia University, 2005.<br>Title from document title page. Document formatted into pages; contains xiv, 256 p. : ill. (some col.). Includes abstract. Includes bibliographical references (p. 118-122).

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13

Nishihara, Munetake. "Low-temperature supersonic flow control using repetitively pulsed MHD force." Columbus, Ohio : Ohio State University, 2006. http://rave.ohiolink.edu/etdc/view?acc%5Fnum=osu1164748794.

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14

Chin, Chee Kian. "Experimental investigation of pitch control enhancement to the flapping wing micro air vehicle." Thesis, Monterey, Calif. : Naval Postgraduate School, 2006. http://bosun.nps.edu/uhtbin/hyperion.exe/06Dec%5FChin.pdf.

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Thesis (M.S. in Engineering Science (Mechanical Engineering))--Naval Postgraduate School, December 2006.<br>Thesis Advisor(s): Kevin D. Jones. "December 2006." Includes bibliographical references (p. 117-118). Also available in print.

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15

Grossir, Guillaume. "Longshot hypersonic wind tunnel flow characterization and boundary layer stability investigations." Doctoral thesis, Universite Libre de Bruxelles, 2015. http://hdl.handle.net/2013/ULB-DIPOT:oai:dipot.ulb.ac.be:2013/209044.

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The hypersonic laminar to turbulent transition problem above Mach 10 is addressed experimentally in the short duration VKI Longshot gun tunnel. Reentry conditions are partially duplicated in terms of Mach and Reynolds numbers. Pure nitrogen is used as a test gas with flow enthalpies sufficiently low to avoid its dissociation, thus approaching a perfect gas behavior. The stabilizing effects of Mach number and nosetip bluntness on the development of natural boundary layer disturbances are evaluated over a 7 degrees half-angle conical geometry without angle of attack. <p><p>Emphasis is initially

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16

Harding, Matthew T. "An experimental investigation of the performance of staggered PIN-FIN Array laminar flow heat exchangers." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2005. http://library.nps.navy.mil/uhtbin/hyperion/05Mar%5FHarding.pdf.

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17

Hobbs, William Bradford. "Piezoelectric energy harvesting: vortex induced vibrations in plants, soap films, and arrays of cylinders." Thesis, Georgia Institute of Technology, 2010. http://hdl.handle.net/1853/33811.

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The goal of this project was to develop a wind generator that utilizes the collective oscillating motion of multiple piezoelectric devices. These devices would be an alternative to rotating turbine designs for low power generation, for use in applications such as remote power generation. A series of inexpensive devices were developed that harvested energy from vortex shedding, both as independent and cooperative devices. The behavior of single devices was studied, but more interestingly, the way that multiple devices arranged together can increase power output was studied. It was shown that i

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18

Paula, Adson Agrico de. "The airfoil thickness effects on wavy leading edge phenomena at low Reynolds number regime." Universidade de São Paulo, 2016. http://www.teses.usp.br/teses/disponiveis/3/3150/tde-27092016-153422/.

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Recently, the wavy leading edge airfoils, inspired by the humpback whale´s flipper, have been investigated, as flow control mechanisms, at low Reynolds numbers in order to improve aerodynamic performance in this particular flow regime. The overall aim of this work is to investigate the airfoil geometric effects on wavy leading edge phenomena in the low Reynolds number regime. Experimental investigations were carried out correlating force measurements with mini-tuft and oil visualizations in order to understand the airfoil thickness effects on wavy leading edge phenomena. Three sets of airfoil

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19

Edy, Jean-Luc. "Application de la photoluminescence pour la mesure des flux thermiques en soufflerie hypersonique à rafales." Valenciennes, 1995. https://ged.uphf.fr/nuxeo/site/esupversions/b8f44f3d-2475-494b-9670-b3b708b9c821.

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Une étude a été entreprise à la direction de l'aérodynamique de l'onera concernant l'application en soufflerie hypersonique d'une nouvelle méthode thermographique utilisant les propriétés de la photoluminescence. Après avoir étudie la faisabilité de la technique en mesure ponctuelle, il a été décidé de développer un système cartographique basé sur l'utilisation d'une camera video 3-ccd et d'un système de traitement d'images et de vérifier son adéquation aux mesures des transferts de chaleur pariétaux dans les souffleries hypersoniques à rafales. Le système a été étalonné en laboratoire, puis é

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20

Malécot, Yann. "Intermittence en turbulence 3D : statistiques de la vitesse et de la vorticité." Université Joseph Fourier (Grenoble), 1998. http://www.theses.fr/1998GRE10177.

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Cette these est une etude experimentale de la turbulence 3d, effectuee dans differentes configurations : turbulence de grille, turbulence de jet et turbulence de soufflerie a tres grand nombre de reynolds. Elle s'attache a caracteriser precisement l'intermittence des ecoulements turbulents, d'une part, d'un point de vue statistique, d'autre part, d'un point de vue structurel. Plusieurs lois, qui concernent en particulier l'universalite de la turbulence, en sont deduites.

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21

Honoré, David. "Fluorescence induite par laser à excimères bande-fine. Application à la caractérisation de souffleries à haute enthalpie." Rouen, 1995. http://www.theses.fr/1995ROUES051.

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Le travail présenté dans ce mémoire concerne le développement de la technique de mesure de fluorescence induite par laser (LIF) à excimères fluorure d'argon bande-fine, et son utilisation pour l'étude expérimentale de jets supersoniques de plasma au voisinage de maquettes immergées dans l'écoulement, simulant les conditions de réentrée atmosphérique d'un engin spatial. Les différents schémas de fluorescence des molécules monoxyde d'azote et monoxyde de carbone sont discutés. La température du milieu est déduite de la comparaison des spectres d'excitation expérimentaux de la bande epsilon de NO

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22

(7399604), Phillip Portoni. "Using Suction for Laminar Flow Control in Hypersonic Quiet Wind Tunnels: A Feasibility Study." Thesis, 2019.

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<div>To reduce the risk of using suction in a hypersonic quiet-tunnel nozzle design, this project tested micro-perforated suction sections to remove the boundary layer on an axisymmetric model in the Boeing/AFOSR Mach-6 Quiet Tunnel. The model was a cone-flare geometry tested at 0° angle of attack. The turn from the 7° half-angle cone to the flare was designed to prevent flow separation. The flare was designed to amplify the Görtler instability.</div><div><br></div><div>Five suction sections were designed with different perforation patterns and porosities. Four were successfully manufactured,

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23

Lu, Guan-hung, and 呂冠鴻. "Using flow visualization and empirical mode decomposition to study numerical wind-wave turbulent flow." Thesis, 2012. http://ndltd.ncl.edu.tw/handle/78367872593997547300.

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碩士<br>國立中央大學<br>水文與海洋科學研究所<br>100<br>An interactive visualization tool and an image procession technique are developed to explore the coherent structures within a turbulent boundary layer bounded by a wind-driven gravity-capillary wave. The flow filed is adopted from direct numerical simulation conducted by Tsai and Hung (2007). The interactive visualization tool is developed using OpenGL, and is capable of visualizing time-evolving, three-dimensional flow field. The image procession method is a combination of conditional phase averaging and the method of empirical mode decomposition developed

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24

Huang-TingJiang and 江皇廷. "Flow Visualization and PIV Measurement of Flow Field around a Vertical Axis Wind Turbine in Dynamic Stall." Thesis, 2015. http://ndltd.ncl.edu.tw/handle/2j42dt.

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25

Swytink-Binnema, Nigel. "Digital Tuft Flow Visualisation of Wind Turbine Blade Stall." Thesis, 2014. http://hdl.handle.net/10012/8459.

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Wind turbines installed in the open atmosphere experience much more complex and highly-varying flow than their counterparts in wind tunnels or numerical simulations. In particular, aerodynamic stall—which occurs often on stall-regulated wind turbines in such variable flow conditions—can affect both wind turbine blade lifespan and noise generation. A field test site was therefore installed at the outer limits of the city of Waterloo, Ontario to study a small-scale 30 kW stall-regulated wind turbine. Experimental equipment was installed to monitor parameters such as wind speed and direction

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26

Comyn, Graeme Ian. "Performance evaluation, wake study, and flow visualization of air and large diameter water droplets around the blade of a micro horizontal axis wind turbine." Master's thesis, 2011. http://hdl.handle.net/10048/1701.

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This thesis presents a performance evaluation of a micro horizontal axis wind turbine, investigates the use of particle image velocimetry (PIV) to capture the flow field around a rotating blade and to track water droplets in the flow. The testing was done in a low speed wind tunnel in a highly blocked configuration. The turbine was instrumented to measure rotational speed of the rotor, axial thrust and power output. Wind speed of the wake was measured with a Kiel probe. Performance characteristics were calculated and compared with the manufacturer’s published data and to power predictions

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27

Philip, Sarah Jobin. "Investigation of Heat Transfer Rates Around the Aerodynamic Cavities on a Flat Plate at Hypersonic Mach Numbers." Thesis, 2011. http://etd.iisc.ernet.in/2005/3900.

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Aerodynamic cavities are common features on hypersonic vehicles which are caused in both large and small scale features like surface defects, pitting, gap in joints etc. In the hypersonic regime, the presence of such cavities alters the flow phenomenon considerably and heating rates adjacent to the discontinuities can be greatly enhanced due to the diversion of flow. Since the 1960s, a great deal of theoretical and experimental research has been carried out on cavity flow physics and heating. However, most of the studies have been done to characterize the effect downstream and within the cavit

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28

Reddeppa, P. "Shock Tunnel Investigations On Hypersonic Separated Flows." Thesis, 2007. http://hdl.handle.net/2005/586.

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Knowledge of flow separation is very essential for proper understanding of both external and internal aerothermodynamics of bodies. Because of unique flow features such as thick boundary layers, merged shock layers, strong entropy layers, flow separation in the flow field of bodies at hypersonic speeds, is both complex as well as interesting. The problem of flow separation is further complicated at very high stagnation enthalpies because of the real gas effects. Notwithstanding the plethora of information available in open literature even for simple geometric configurations the experimentally

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29

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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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 wa

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30

Kumar, Chintoo Sudhiesh. "Experimental Investigation Of Aerodynamic Interference Heating Due To Protuberances On Flat Plates And Cones Facing Hypersonic Flows." Thesis, 2013. http://etd.iisc.ernet.in/handle/2005/2621.

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With the age of hypersonic flight imminent just beyond the horizon, researchers are working hard at designing work-arounds for all the major problems as well as the minor quirks associated with it. One such issue, seemingly innocuous but one that could be potentially deadly, is the problem of interference heating due to surface protuberances. Although an ideal design of the external surfaces of a high-speed aircraft dictates complete smoothness to reduce drag, this is not always possible in reality. Control surfaces, sheet joints, cable protection pads etc. generate surface discontinuities of

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31

Thakur, Ruchi. "Experimental Analysis of Shock Stand off Distance over Spherical Bodies in Hypersonic Flows." Thesis, 2015. http://etd.iisc.ernet.in/2005/3848.

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One of the characteristics of the high speed ows over blunt bodies is the detached shock formed in front of the body. The distance of the shock from the stagnation point measured along the stagnation streamline is termed as the shock stand o distance or the shock detachment distance. It is one of the most basic parameters in such ows. The need to know the shock stand o distance arises due to the high temperatures faced in these cases. The biggest challenge faced in high enthalpy ows is the high amounts of heat transfer to the body. The position of the shock is relevant in knowing the temperatu

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