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Dissertations / Theses on the topic 'Tip Vortexes'

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Published: 3 June 2025

Last updated: 31 July 2025

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1

Affes, Habib. "Tip-vortex/airframe interactions /." The Ohio State University, 1992. http://rave.ohiolink.edu/etdc/view?acc_num=osu1487777170407828.

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2

Margaris, Panagiotis. "Wing tip vortex control by means of tip blowing." Thesis, University of Bath, 2006. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.436750.

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3

Dedekarginoglu, Riza Can. "A Parametric Investigation Of Tip Injection For Active Tip Vortex Control." Master's thesis, METU, 2010. http://etd.lib.metu.edu.tr/upload/12612703/index.pdf.

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ABSTRACT A PARAMETRIC INVESTIGATION OF TIP INJECTION FOR ACTIVE TIP VORTEX CONTROL Dedekarginoglu, Riza Can M.Sc., Department of Aerospace Engineering Supervisor :Asst. Prof. Dr. Oguz Uzol December 2010, 79 pages Wing tip vortex is a challenging phenomenon that reduces the lift generation at the tip region of the wing. For aerial vehicles, several methodologies were presented for the sake of controlling vortices and alleviating effects of tip loss. In this study, the effect of wing tip injection on wing tip vortex structure was investigated computationally. A NACA0015 profile rectangular wing

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4

Pentelow, Steffen L. "Wing-tip Vortex Structure and Wandering." Thèse, Université d'Ottawa / University of Ottawa, 2014. http://hdl.handle.net/10393/31114.

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An isolated wing-tip vortex from a square-tipped NACA 0012 wing at an angle of attack of 5 degrees was studied in a water tunnel at a chord based Reynolds number of approximately 24000. Measurements were taken using stereo particle image velocimetry at three measurement planes downstream of the wing under each of three freestream turbulence conditions. The amplitude of wandering of the vortex axis increased with increasing distance downstream of the wing and with increasing freestream turbulence intensity. The magnitude of the peak azimuthal velocity decreased with increasing distance from

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5

Ghimire, Hari Charan. "WING-TIP VORTEX EVOLUTION IN TURBULENCE." UKnowledge, 2018. https://uknowledge.uky.edu/me_etds/110.

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Planar and stereo particle image velocimetry measurements were conducted of a wing-tip vortex decaying in free-stream turbulence in order to understand the evolution of a vortex and its decay mechanism. The vortex decayed faster in the presence of turbulence. The decay of the circulation was found to be almost entirely due to a decrease in circulation of the vortex core, caused by the relative decrease in peak tangential velocity without a corresponding increase in core radius. These events were found to be connected with the stripping of core fluid from the vortex core. The increased rate of

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6

Ostovan, Yashar. "Experimental Investigation Of Waveform Tip Injection Onthe Characteristics Of The Tip Vortex." Master's thesis, METU, 2011. http://etd.lib.metu.edu.tr/upload/12613780/index.pdf.

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This study investigates the effect of chordwisely modulated tip injection on the flow and turbulence characteristics of the tip vortex through experimental measurements downstream of a rectangular half-wing that has an aspect ratio of three. This injection technique involves spanwise jets at the tip that are issued from a series of holes along the chord line normal to the freestream flow direction. The injection mass flow rate from each hole is individually controlled using computer driven solenoid valves and therefore the flow injection geometrical pattern at the tip can be adjusted to any de

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7

Pereira, Jennifer Loren. "Experimental investigation of tip vortex control using a half delta shaped tip strake." Thesis, McGill University, 2012. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=107592.

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The effectiveness of using a half delta wing tip strake for static wing tip vortex control and performance enhancement was investigated. The flowfield over the wingtip and in the near-field was studied over a low aspect ratio NACA 0012 wing fitted with a half delta wing with a leading-edge sweep of 64º at a chord Reynolds number of 3 x 10⁵. The incidence of the strake relative to the main wing was movable allowing for strake settings from δ = -10º to +10º. Force balance data supplemented with flowfield measurements were used to investigate the performance improvements with the addition of the

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8

Duraisamy, Karthikeyan. "Studies in tip vortex formation, evolution and control." College Park, Md. : University of Maryland, 2005. http://hdl.handle.net/1903/2372.

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Thesis (Ph. D.) -- University of Maryland, College Park, 2005.<br>Thesis research directed by: Aerospace Engineering. Title from t.p. of PDF. Includes bibliographical references. Published by UMI Dissertation Services, Ann Arbor, Mich. Also available in paper.

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9

Zsoldos, Jeffrey S. "An experimental investigation of interacting wing-tip vortex pairs." Thesis, This resource online, 1992. http://scholar.lib.vt.edu/theses/available/etd-11242009-020215/.

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10

Heckel, Scott P. "Reynolds stress measurements in a turbine tip leakage vortex." Thesis, This resource online, 1992. http://scholar.lib.vt.edu/theses/available/etd-10102009-020346/.

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11

Hart, Douglas P. Acosta Allan J. Brennen Christopher E. "Cavitation and wake structure of unsteady tip vortex flows /." Diss., Pasadena, Calif. : California Institute of Technology, 1993. http://resolver.caltech.edu/CaltechETD:etd-03272007-131947.

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12

Marinelli, Andrea T. "Biologically Inspired Wing Tip Geometry Optimization." Digital WPI, 2010. https://digitalcommons.wpi.edu/etd-theses/805.

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Wingtip vortices are an important problem in aerodynamic and hydrodynamic engineering because of their contribution to induced drag, tip cavitation, and wake turbulence. These effects decrease equipment efficiency and lifespan, which increases application costs. Biology provides an inspiring solution to this problem in avian flight through the spreading of primary feathers. Previous studies have shown increased lift to drag ratio and efficiency of wings and propeller blades through modified wingtip geometry. The goal of this project is to optimize the tip geometry (primary feather angle) o

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13

Thompson, Thomas L. "Velocity measurements near the blade tip and in the tip vortex core of a hovering model rotor." Diss., Georgia Institute of Technology, 1986. http://hdl.handle.net/1853/13003.

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14

Elson, Tom. "Computational aerodynamics for open rotor tip vortex interaction noise prediction." Thesis, Cranfield University, 2015. http://dspace.lib.cranfield.ac.uk/handle/1826/12294.

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Open rotor engines can provide fuel savings of up to twenty seven percent compared to a modern high bypass turbofan engine. They were subject to intense research in the 1980s in response to the 1973 oil crisis. They have come back into consideration to combat the strict environmental regulations currently imposed on the aviation industry and to meet the ACARE 2020 requirements. Recent large scale European projects such as DREAM and Clean Sky have included signi cant research on the open rotor since their comeback. Their major drawback is the noise levels generated when the wake and tip vortice

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15

Engel, Mark A. "A wind tunnel investigation of a wing-tip trailing vortex." Thesis, This resource online, 1995. http://scholar.lib.vt.edu/theses/available/etd-01102009-063459/.

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16

Fournis, Camille. "Study of tip clearance flows." Thesis, KTH, Flygdynamik, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-244423.

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The tip leakage vortex is responsible for the generation of stagnation pressure losses inside the compressor along with the outbreak of rotating stall and surge. The current paper analytically proved that a part of the losses is proportional to the vortex circulation squared. The evolution of this circulation has been investigated as part of a parametric study which tested several clearance heights. The work consists in adopting a simplified single blade configuration to study the physics of the flow by means of wind tunnel experiments and numerical calculations. Upon visualising the main feat

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17

Odemark, Ylva. "Wakes behind wind turbines - Studies on tip vortex evolution and stability." Licentiate thesis, KTH, Mekanik, 2012. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-93806.

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The increased fatigue loads and decreased power output of a wind turbine placed in the wake of another turbine is a well-known problem when building new wind power farms. In order to better estimate the total power output of a wind power farm, knowledge about the development and stability of wind turbine wakes is crucial. In the present thesis, the wake behind a small-scale model turbine was investigated experimentally in a wind tunnel. The velocity in the wake was measured with hot-wire anemometry, for different free stream velocities and tip speed ratios. To characterize the behaviour of the

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18

Vasilescu, Roxana. "Helicopter blade tip vortex modifications in hover using piezoelectrically modulated blowing." Diss., Available online, Georgia Institute of Technology, 2004:, 2004. http://etd.gatech.edu/theses/available/etd-11192004-165246/unrestricted/vasilescu%5Froxana%5F200412%5Fphd.pdf.

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Thesis (Ph. D.)--Aerospace Engineering, Georgia Institute of Technology, 2005.<br>Dancila, Stefan, Committee Chair ; Sankar, Lakshmi, Committee Member ; Ruzzene, Massimo, Committee Member ; Smith, Marilyn, Committee Member ; Yu, Yung, Committee Member. Vita. Includes bibliographical references.

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19

Mercan, Bayram. "Experimental Investigation Of The Effects Of Waveform Tip Injection On The Characteristics Of Tip Leakage Vortex In A Lpt Cascade." Master's thesis, METU, 2012. http://etd.lib.metu.edu.tr/upload/12614111/index.pdf.

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This study presents the results of an experimental study that investigates the effects of uniform/waveform tip injection along the camberline on the total pressure loss characteristics downstream of a row of Low Pressure Turbine (LPT) blades. The experiments are performed in a low speed cascade facility. This injection technique involves spanwise jets at the tip that are issued from a series of holes along the camber line normal to the freestream flow direction. The injection mass flow rate from each hole is individually controlled using computer driven solenoid valves and therefore the flow i

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20

Martin, David Stewart. "An Investigation of Avian Wing Tip Vortex Generation Using a Biomimetic Approach." DigitalCommons@CalPoly, 2017. https://digitalcommons.calpoly.edu/theses/1734.

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An experimental study has been conducted to develop a process allowing the creation of biologically accurate aerodynamic test models mimicking the slotted primary feather geometry of the Brown Pelican (Pelecanus occidentalis). Preserved examples of both a full Brown Pelican wing and a single primary feather were 3D scanned and digitally reconstructed using a combination of MATLAB and CAD software. The final model was then 3D printed as a collection of smaller components using a LulzBot TAZ 6 printer and Taulman3D T-Glase PET filament. After using various surface finishing techniques to improve

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21

Najarzadegan, Farshid. "Circulation Dependence of the Interaction Between a Wing-Tip Vortex and Turbulence." UKnowledge, 2019. https://uknowledge.uky.edu/me_etds/145.

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Vortices are present in many fluid flows and depending on the context they may be either beneficial or harmful for different systems or processes. Planar particle image velocimetry was used to examine the vortex evolution and its decay under different turbulence intensities and vortex circulation. The vortex decayed faster in the presence of high turbulence intensity. Vortex trajectories were impacted by turbulence intensity and vortex strength. Trajectories with no turbulence intensity had less variation. The vortex wandering amplitude decreased with growth of vortex strength. The vortex deca

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22

Wong, Oliver D. "Formation and evolution of tip vortices of an isolated rotor in forward flight." Diss., Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/12377.

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23

Pashias, Christos. "Propeller tip vortex simulation using adaptive grid refinement based on flow feature identification." Thesis, University of Southampton, 2005. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.427353.

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24

Cho, Donald L. (Donald Lee). "Effect of vortex core stagnation pressure on tip clearance flow blockage in turbomachines." Thesis, Massachusetts Institute of Technology, 1995. http://hdl.handle.net/1721.1/47391.

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25

Brewer, Wesley Huntington. "On simulating tip-leakage vortex flow to study the nature of cavitation inception." Diss., Mississippi State : Mississippi State University, 2002. http://library.msstate.edu/etd/show.asp?etd=etd-04102002-134949.

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26

Tian, Qing. "Near Wall Behavior of Vortical Flow around the Tip of an Axial Pump Rotor Blade." Diss., Virginia Tech, 2006. http://hdl.handle.net/10919/30062.

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This dissertation presents the results from an experimental study of three-dimensional turbulent tip gap flow in a linear cascade wind tunnel with 3.3% chord tip clearance with and without moving endwall simulation. Experimental measurements have been completed in Virginia Tech low speed linear cascade wind tunnel. A 24" access laser-Doppler velocimeter (LDV) system was developed to make simultaneous three-velocity-component measurements. The overall size of the probe is 24"Ã 37"Ã 24"and measurement spatial resolution is about 100 Î¼m. With 24" optical access distance, the LDV probe allows mea

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27

Intaratep, Nanyaporn. "Formation and Development of the Tip Leakage Vortex in a Simulated Axial Compressor with Unsteady Inflow." Diss., Virginia Tech, 2006. http://hdl.handle.net/10919/26771.

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The interaction between rotor blade tip leakage vortex and inflow disturbances, such as encountered in shrouded marine propulsors, was simulated in the Virginia Tech Linear Cascade Wind Tunnel equipped with a moving endwall system. Upstream of the blade row, idealized periodic inflow unsteadiness was generated using vortex generator pairs attached to the endwall at the same spacing as the blade spacing. At three tip gap settings, 1.7%c, 3.3%c and 5.7%c, the flow near the lower endwall of the center blade passage was investigated through three-component mean velocity and turbulence distribution

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28

Lenglin, Geoffroy (Geoffroy Philippe) 1976. "Characterization of wake- and tip-vortex-induced unsteady blade response in multistage compressor environment." Thesis, Massachusetts Institute of Technology, 2002. http://hdl.handle.net/1721.1/82227.

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29

Miranda, Alice. "Numerical simulations of the wing wake and tip vortex for air-to-air refuelling." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/10236.

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The present research was carried out in the framework of the ASTRAEA II project, in collaboration with Cobham Mission Equipment. One part of the overall ASTRAEA II project is to design an autonomous air-refuelling system based on a wake model computed in real-time, which allows the flow field to be visualised in a Synthetic Environment. In a previous part of the ASTRAEA project a MATLAB® code was developed based on the extended lifting line method (referred to as the ELL code) which provides a refuelling tanker wake model. The aim of this project is to understand the tanker wake, to provide mo

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30

Wells, Jesse Buchanan. "Effects of Turbulence Modeling on RANS Simulations of Tip Vortices." Thesis, Virginia Tech, 2009. http://hdl.handle.net/10919/34343.

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The primary purpose of this thesis is to quantify the effects of RANS turbulence modeling on the resolution of free shear vortical flows. The simulation of aerodynamic wing-tip vortices is used as a test bed. The primary configuration is flow over an isolated finite wing with aspect ratio, , and Reynolds number, . Tip-vortex velocity profiles, vortex core and wake turbulence levels, and Reynolds stresses are compared with wind tunnel measurements. Three turbulence models for RANS closure are tested: the Lumley, Reece, and Rodi full Reynolds stress transport model and the Sparlart-Allmaras

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31

Tian, Qing. "Some Features of Tip Gap Flow Fields of a Linear Compressor Cascade." Thesis, Virginia Tech, 2003. http://hdl.handle.net/10919/9673.

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This thesis presents some results from an experimental study of three-dimensional turbulent tip gap flows in the linear cascade wind tunnel, for two different tip gap clearances (t/c=1.65% and 3.3%). The experiments focus on near-wall flow field measurements for the stationary wall and moving wall, and static pressure measurement on the low end-wall for the stationary wall case. The representative flows were pressure driven, three-dimensional turbulent boundary layers in the linear cascade tunnel for the stationary wall case, and the combination of the pressure driven and shear driven flow for

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32

Shin, Sangmook. "Reynolds-Averaged Navier-Stokes Computation of Tip Clearance Flow in a Compressor Cascade Using an Unstructured Grid." Diss., Virginia Tech, 2001. http://hdl.handle.net/10919/28947.

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A three-dimensional unstructured incompressible RANS code has been developed using artificial compressibility and Spalart-Allmaras eddy viscosity model. A node-based finite volume method is used in which all flow variables are defined at the vertices of tetrahedrons in an unstructured grid. The inviscid fluxes are computed by using the Roe's flux difference splitting method, and higher order accuracy is attained by data reconstruction based on Taylor series expansion. Gauss theorem is used to formulate necessary gradients. For time integration, an implicit scheme based on linearized Euler back

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33

Ma, Ruolong. "Unsteady Turbulence Interaction in a Tip Leakage Flow Downstream of a Simulated Axial Compressor Rotor." Diss., Virginia Tech, 2003. http://hdl.handle.net/10919/28060.

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The unsteady behavior of a tip leakage flow downstream of a simulated axial compressor rotor has been studied. The Virginia Tech low speed linear cascade wind tunnel was adapted to model the unsteady tip leakage flow produced by a rotor operating in the vortical wakes of a set of stator vanes. The cascade, consisting of 8 GE rotor B blades, has adjustable tip gap, inlet angle of 65.1 degrees, turning angle of 11.8 degrees and solidity of 1.076. The cascade Reynolds number, based on blade chord, was 393,000. A moving end wall was used to simulate the relative motion between rotor and casing, an

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34

Li, Bo. "Aerodynamic and acoustic analysis of the tip-leakage flow past a single ailfoil." Thesis, Lyon, 2016. http://www.theses.fr/2016LYSEC042/document.

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L'écoulement de jeu est un phénomène très important dans les turbomachines. Il provient du mouvement relatif entre la pale et la paroi d'extrémité, et la différence de pression à travers la pale. L'écoulement de jeu est extrêmement complexe pour sa nature tridimensionnelle et instable, et son existence conduit à de nombreux effets défavorables, par exemple, les pertes de performance aérodynamique et les émissions de bruit. C'est pourquoi l'écoulement de jeu a motivé de nombreuses recherches expérimentales et numériques. Afin d'améliorer la compréhension du écoulement de jeu et le bruit de larg

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35

Tang, Genglin. "Measurements of the Tip-gap Turbulent Flow Structure in a Low-speed Compressor Cascade." Diss., Virginia Tech, 2003. http://hdl.handle.net/10919/11178.

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This dissertation presents results from a thorough study of the tip-gap turbulent flow structure in a low-speed linear compressor cascade wind tunnel at Virginia Tech that includes a moving belt system to simulate the relative motion between the tip and the casing. The endwall pressure measurements and the surface oil flow visualizations were made on a stationary endwall to obtain the flow features and to determine the measurement profiles of interest. A custom-made miniature 3-orthogonal-velocity-component fiber-optic laser-Doppler velocimetry (LDV) system was used to measure all three compon

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36

Lundin, Lukas. "Tip vortex cavitation and diffused vorticity of propeller profiles: a modelling approach : Investigation of an implemented TVI model, and implementation and investigation of a DVH model." Thesis, Karlstads universitet, Institutionen för ingenjörsvetenskap och fysik, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:kau:diva-65102.

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To predict fluid properties and interactions is an important task for the industry. It is plagued, however, by being close to impossible to predict analytically. Hence, it is customary to turn to numerical solutions. This in itself comes with many different methods and approaches suitable for different needs. This work focuses on two methods: Tip Vortex Index (TVI) and Diffused Vortex Hydrodynamics (DVH). TVI is a method to predict when a marine propeller will experience cavitation of tip vortices and is based on calculations from a Boundary Element Method (BEM). DVH is a particle method for s

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37

Lee, Daniel H. "Numerical Investigation on the Effects of Self-Excited Tip Flow Unsteadiness and Blade Row Interactions on the Performance Predictions of Low Speed and Transonic Compressor Rotors." University of Cincinnati / OhioLINK, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1380620247.

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38

Riera, William. "Evaluation of the ZDES method on an axial compressor : analysis of the effects of upstream wake and throttle on the tip-leakage flow." Thesis, Ecully, Ecole centrale de Lyon, 2014. http://www.theses.fr/2014ECDL0030/document.

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L’écoulement de jeu dans les compresseurs axiaux est étudié à l’aide de la Zonal Detached Eddy Simulation (ZDES). L’objectif consiste à évaluer la capacité de méthodes hybrides URANS/LES à simuler l’écoulement de jeu d’un compresseur axial réaliste afin de mieux comprendre la physique de cet écoulement, notamment son comportement au vannage ainsi que l’effet de sillages venant du stator amont sur le rotor aval. Après avoir choisi la méthode hybride ZDES, un banc d’essai numérique est défini afin de simuler le premier rotor du compresseur de recherche CREATE. Ce banc a la particularité de pouvo

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39

Murray, Henry Hall IV. "Turbulence and Sound Generated by a Rotor Operating Near a Wall." Thesis, Virginia Tech, 2016. http://hdl.handle.net/10919/71332.

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Acoustic and aerodynamic measurements have been carried out on a rotor operating in a planar turbulent boundary layer near a wall for a variety of thrust conditions and yaw angles with respect to the inflow. At the highest thrust condition a strong flow reversal in the wall-rotor tip gap was observed. Average velocity fields filtered by the angular position of the rotor show that the flow reversal is fed by jets of fluid that tend to form below the blade as it passes by the wall. Instantaneous velocity measurements show the presence of strong vortices in the tip gap. These vortices were ch

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40

Geiger, Derek Henry. "Comparative Analysis of Serrated Trailing Edge Designs on Idealized Aircraft Engine Fan Blades for Noise Reduction." Thesis, Virginia Tech, 2004. http://hdl.handle.net/10919/40542.

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The effects of serrated trailing edge designs, designed for noise reduction, on the flow-field downstream of an idealized aircraft engine fan blade row were investigated in detail. The measurements were performed in the Virginia Tech low speed linear cascade tunnel on one set of baseline GE-Rotor-B blades and four sets of GE-Rotor-B blades with serrated trailing edges. The four serrated blade sets consisted of two different serration sizes (1.27 cm and 2.54 cm) and for each different serration size a second set of blades with added trailing edge camber. The cascade row consisted of 8 GE-Rotor-

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41

Kuhl, David Derieg. "Near Wall Investigation of Three Dimensional Turbulent Boundary Layers." Thesis, Virginia Tech, 2001. http://hdl.handle.net/10919/34676.

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This report documents the experimental study for four different three-dimensional turbulent flows. The investigation focuses on near wall measurements in these flows. Several experimental techniques are used in the studies; however, the bulk of the investigation focuses on a three-orthogonal-velocity-component fiber-optic laser Doppler anemometer (3D-LDA) system. The control volume of the 3D-LDA is on the order of 50 micro-meter in size, or a y<sup>+</sup> distance of around 2.3 units (using average values of U<sub>&#964</sub> and ν from the experiment). An auxiliary small boundary laye

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42

MIORINI, Rinaldo Luigi. "Investigations on the flow inside pumps by means of 2D particle image velocimetry." Doctoral thesis, Università degli studi di Bergamo, 2010. http://hdl.handle.net/10446/615.

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This work is concerned with the sampling, evaluating and critically interpreting of fuid dynamics phenomena inside two radically different pumps. Large scale flow structures are investigated in the vaned diffuser of a centrifugal pump and in the rotor passage of a water jet axial pump by means of two-dimensional particle image velocimetry (2DPIV). In the first part of the work, a centrifugal pump is run at various capacities to derive information about the flow around the diffuser vanes. Preliminarily, time resolved pressure measurements have indicated the presence of very large scale non-pe

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43

Kníř, Jakub. "Parametrická studie vlivu tvaru štěrbiny mezi lopatkou rotoru turbíny a skříní motoru na aerodynamické vlastnosti rotoru." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2013. http://www.nusl.cz/ntk/nusl-230820.

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Tato diplomová práce otevírá otázku možnosti zlepšení vlastností kompresoru za pomoci numerické simulace proudění. Hlavním cílem je zvýšení operačního rozsahu na jednom stupni axiálního kompresoru s využitím zařízení pro pasivní kontrolu proudu umístěných ve skříni kompresoru. Prvně bylo prověřeno chování víru ve štěrbině mezi lopatkou a skříní následně celkové charakteristiky původního rotoru. Při snižování hmotnostního průtoku simulace odhalila zvýšený vliv koncového výru na hlavní proud. Navíc byl největší koncový vír v režimu blízkém odtrhávání proudění. Z tohoto důvodu byly pro kontrolu k

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44

Margalida, Gabriel. "Analyse expérimentale et contrôle actif de l'écoulement dans un compresseur axial mono-étagée durant la transition vers le décrochage tournant." Thesis, Paris, ENSAM, 2019. http://www.theses.fr/2019ENAM0039.

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Durant la dernière décennie, le secteur aéronautique n’a cessé de croître et le nombre de passagers transportés a considérablement augmenté. En parallèle, des politiques de plus en plus restrictives ont été mises en place afin de diminuer notre impact environnemental notamment en réduisant les émissions de CO2. Dans cette optique, les motoristes cherchent à concevoir des moteurs plus efficaces, conduisant à l’utilisation de points de fonctionnement plus proches des limites d’opération et a un chargement des étages de compression plus important. Cependant, ces zones étant sensibles au déclenche

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45

Oliveira, Tarciso Mesquita de. "Picos da magnetização em supercondutores do tipo II." [s.n.], 2005. http://repositorio.unicamp.br/jspui/handle/REPOSIP/278497.

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Orientador: Oscar Ferreira de Lima<br>Dissertação (mestrado) - Universidade Estadual de Campinas, Instituto de Fisica Gleb Wataglin<br>Made available in DSpace on 2018-09-24T18:20:24Z (GMT). No. of bitstreams: 1 Oliveira_TarcisoMesquitade_M.pdf: 3236428 bytes, checksum: f8799c6f4d4ac1a196ca499b0ad67efb (MD5) Previous issue date: 2005<br>Resumo: Nesta tese estudamos possíveis origens do Segundo Pico da Magnetização (SPM) em supercondutores de alta e baixa temperatura crítica, usando amostras monocristalinas de Bi2Sr2CaCu2O8+d e de Nb. Para estudar o SPM fizemos medidas de curvas de magnetizaç

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Joulain, Antoine. "Simulation aérodynamique d'extrémités de pales de rotors sustentateurs d'hélicoptère." Thesis, Aix-Marseille, 2015. http://www.theses.fr/2015AIXM4768.

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L’aérodynamique de l’hélicoptère est fortement impactée par les tourbillons générés aux extrémités de pales. La complexité des phénomènes en jeux et l’insuffisance de données expérimentales locales font du design d’extrémité un véritable défi. Cette étude propose une nouvelle approche dédiée à l’étude des extrémités en vol stationnaire. Une méthode numérique rapide et précise est mise au point afin d’étudier une extrémité de pale en rotation comme une extrémité d’aile fixe. Chaque étape de la construction de la méthode est validée par des comparaisons détaillées avec des données expérimentales

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Yang, Cheng-Tsair, and 楊正財. "Study on Tip-Vortex Flow and Tip-Vortex Cavitation." Thesis, 1994. http://ndltd.ncl.edu.tw/handle/61343732885468568254.

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Karpatne, Anand 1987. "Investigation of tip vortex aperiodicity in hover." Thesis, 2012. http://hdl.handle.net/2152/ETD-UT-2012-08-6278.

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Previous research has indicated aperiodicity in the positions of tip vortices emitted from a helicopter rotor blade in hover. The objective of the current study is to develop an analysis of the tip vortex aperiodicity in hover and to validate it with measurements on a reduced-scale, 1m diameter, four-bladed rotor. A “vortex ring emitter model” (VREM) was developed to study the statistics of the tip vortices emitted from a rotor blade during hover. In order to better model the rotor wake, a number of independent vortex blobs were used to describe a vortex ring. An empirical model for viscosity

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chun, Chen chi, and 陳紀川. "Numerical Investigation of the tip vortex flow." Thesis, 2001. http://ndltd.ncl.edu.tw/handle/15380940782800817964.

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碩士<br>國立臺灣大學<br>造船及海洋工程學研究所<br>89<br>Tip Vortex flow of a finite-span hydrofoil at high Reynolds number is numerically investigated by solving the Reynolds-Averaged-Navier-Stokes equations. The tip vortex flow is computed for three angles of attack. The numerical results are compared with the experimental measurements performed in a cavitation tunnel. Core center trajectory has a good agreement with the measurement. Streamline tracing shows similar flow pattern on the pressure side, suction side and tip end as demonstrated by the experiment. It explains roll-up phenomena at the tip of hydrofoi

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Whitehead, Edward J. "The stability of multiple wing-tip vortices." 2010. http://hdl.handle.net/2440/57899.

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Over the last forty or so years interest in the study of wing-tip vortices has increased, primarily due to the introduction of larger passenger aircraft and their subsequent interaction with smaller aircraft. The vortices generated by these larger aircraft present a problem in two main areas; the wake hazard problem, where other aircraft can be subjected to the large tangential velocities of the vortex, and the interaction with ground based features of vortices created during landing and take-off. The first of these is particularly dangerous close to the ground when aircraft are in a high lift

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