Bibliographies thématiques / Vortex-motion. Leading edges (Aerodynamics)

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Littérature scientifique sur le sujet « Vortex-motion. Leading edges (Aerodynamics) »

Auteur : Grafiati
Publié le 4 juin 2021
Mis à jour le 12 février 2022

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Articles de revues sur le sujet "Vortex-motion. Leading edges (Aerodynamics)"

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Buzica, Andrei, Lisa Debschütz, Florian Knoth, and Christian Breitsamter. "Leading-Edge Roughness Affecting Diamond-Wing Aerodynamic Characteristics." Aerospace 5, no. 3 (2018): 98. http://dx.doi.org/10.3390/aerospace5030098.

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Diamond wing configurations for low signature vehicles have been studied in recent years. Yet, despite numerous research on highly swept, sharp edged wings, little research on aerodynamics of semi-slender wings with blunt leading-edges exists. This paper reports on the stall characteristics of the AVT-183 diamond wing configuration with variation of leading-edge roughness size and Reynolds number. Wind tunnel testing applying force and surface pressure measurements are conducted and the results presented and analysed. For the investigated Reynolds number range of 2.1 × 10 6 ≤ R e ≤ 2.7 × 10 6
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Zhao, Hong Yan, Peng Fei Zhang, and Yun Ma. "The Influence of the Flight Aerodynamic for Interactions of Wings and Body of the Honeybee." Applied Mechanics and Materials 670-671 (October 2014): 700–704. http://dx.doi.org/10.4028/www.scientific.net/amm.670-671.700.

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The flight mechanism of flapping-wing was studied by using the translation-rotation model. We established the flapping-coordinate of the wing, gave the equation of the motion, and simplified the flapping-wing model. The aerodynamic and vortices were simulated by the CFD software of Fluent. The leading-edge vortex generated in the translation phase, and delayed stall mechanism had an important effect on the high lift. In the rotation phase, lift peaks appear due to the wing rapidly rotating and rotational circulation mechanism. The aerodynamics were obtained in different amplitudes, frequencies
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Willmott, Alexander P., Charles P. Ellington, and Adrian L. R. Thomas. "Flow visualization and unsteady aerodynamics in the flight of the hawkmoth, Manduca sexta." Philosophical Transactions of the Royal Society of London. Series B: Biological Sciences 352, no. 1351 (1997): 303–16. http://dx.doi.org/10.1098/rstb.1997.0022.

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The aerodynamic mechanisms employed durng the flight of the hawkmoth, Manduca sexta , have been investigated through smoke visualization studies with tethered moths. Details of the flow around the wings and of the overall wake structure were recorded as stereophotographs and high–speed video sequences. The changes in flow which accompanied increases in flight speed from 0.4 to 5.7 m s −1 were analysed. The wake consists of an alternating series of horizontal and vertical vortex rings which are generated by successive down– and upstrokes, respectively. The downstroke produces significantly more
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Viswanath, P. R., and S. R. Patil. "Aerodynamic characteristics of delta wing–body combinations at high angles of attack." Aeronautical Journal 98, no. 975 (1994): 159–70. http://dx.doi.org/10.1017/s0001924000049848.

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AbstractAn experimental study investigating the aerodynamic characteristics of generic delta wing-body combinations up to high angles of attack was carried out at a subsonic Mach number. Three delta wings having sharp leading edges and sweep angles of 50°, 60° and 70° were tested with two forebody configurations providing a variation of the nose fineness ratio. Measurements made included six-component forces and moments, limited static pressures on the wing lee-side and surface flow visualisation studies. The results showed symmetric flow features up to an incidence of about 25°, beyond which
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Saputra, Do Young Byun, Yung Hwan Byun, and Hoon Cheol Park. "Experimental and Numerical Study on Flapping Wing Kinematics and Aerodynamics of Coleoptera." Key Engineering Materials 326-328 (December 2006): 175–78. http://dx.doi.org/10.4028/www.scientific.net/kem.326-328.175.

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In this study we have experimentally and numerically analyzed the flapping mechanism and wing kinematics of coleoptera (Propylea japonica Thunberg). Using digital high speed camera, we captured the continuous wing kinematics and visualized the flight motion of the free-flying coleoptera. The experimental visualization shows that the elytra flapped concurrently with the main wing both in the downstroke and upstroke motions. In order to define the wing kinematics of coleoptera, the displacement of a wing cross section (50% span-wise) was measured for each sequence of the wing motion. Using these
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Liu, H., C. P. Ellington, K. Kawachi, C. van den Berg, and A. P. Willmott. "A computational fluid dynamic study of hawkmoth hovering." Journal of Experimental Biology 201, no. 4 (1998): 461–77. http://dx.doi.org/10.1242/jeb.201.4.461.

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A computational fluid dynamic (CFD) modelling approach is used to study the unsteady aerodynamics of the flapping wing of a hovering hawkmoth. We use the geometry of a Manduca sexta-based robotic wing to define the shape of a three-dimensional 'virtual' wing model and 'hover' this wing, mimicking accurately the three-dimensional movements of the wing of a hovering hawkmoth. Our CFD analysis has established an overall understanding of the viscous and unsteady flow around the flapping wing and of the time course of instantaneous force production, which reveals that hovering flight is dominated b
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Lamar, J. "A career in vortices and edge forces." Aeronautical Journal 116, no. 1176 (2012): 101–52. http://dx.doi.org/10.1017/s0001924000006667.

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Abstract This lecture recognises the background and distinguished work of Frederick William Lanchester, and notes that my background has a few similarities with his. These include a shared interest in wings, lift and vortices. My career at the NASA Langley Research Center spans the time-frame from America’s Super Sonic Transport through 2009. An early emphasis involved wind-tunnel testing of research aircraft models and the development of computer codes for subsonic aerodynamics of wing planforms. These attached-flow codes were applied to various configurations, including those with variable-s
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Ellington, C. P. "The novel aerodynamics of insect flight: applications to micro-air vehicles." Journal of Experimental Biology 202, no. 23 (1999): 3439–48. http://dx.doi.org/10.1242/jeb.202.23.3439.

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The wing motion in free flight has been described for insects ranging from 1 to 100 mm in wingspan. To support the body weight, the wings typically produce 2–3 times more lift than can be accounted for by conventional aerodynamics. Some insects use the fling mechanism: the wings are clapped together and then flung open before the start of the downstroke, creating a lift-enhancing vortex around each wing. Most insects, however, rely on a leading-edge vortex (LEV) created by dynamic stall during flapping; a strong spanwise flow is also generated by the pressure gradients on the flapping wing, ca
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Thielicke, William, and Eize J. Stamhuis. "The influence of wing morphology on the three-dimensional flow patterns of a flapping wing at bird scale." Journal of Fluid Mechanics 768 (March 4, 2015): 240–60. http://dx.doi.org/10.1017/jfm.2015.71.

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The effect of airfoil design parameters, such as airfoil thickness and camber, are well understood in steady-state aerodynamics. But this knowledge cannot be readily applied to the flapping flight in insects and birds: flow visualizations and computational analyses of flapping flight have identified that in many cases, a leading-edge vortex (LEV) contributes substantially to the generation of aerodynamic force. In flapping flight, very high angles of attack and partly separated flow are common features. Therefore, it is expected that airfoil design parameters affect flapping wing aerodynamics
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Han, Jong-Seob, Jo Won Chang, and Jae-Hung Han. "The advance ratio effect on the lift augmentations of an insect-like flapping wing in forward flight." Journal of Fluid Mechanics 808 (November 3, 2016): 485–510. http://dx.doi.org/10.1017/jfm.2016.629.

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Time-varying force/moment measurements and digital particle image velocimetry (DPIV) were conducted to reveal the influence of an advance ratio $J$ on an insect-like flapping wing. A scaled-up robotic model and a servo-driven towing tank were employed to investigate nine individual $J$ cases – $J=0$ (hovering), 0.0625, 0.1250, 0.1875, 0.25, 0.50, 0.75, 1.0 and $\infty$ (gliding motion) – at a high Reynolds number ($Re\sim 10^{4}$). At $J\leqslant 0.25$, the aerodynamic forces slightly increased from those in hover ($J=0$). The centres of pressure in these cases were concentrated in the outboar
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Thèses sur le sujet "Vortex-motion. Leading edges (Aerodynamics)"

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Pino, Romainville Francisco Adolfo. "The effect of adding multiple triangular vortex generators on the leading edge of a wing." Morgantown, W. Va. : [West Virginia University Libraries], 2005. https://eidr.wvu.edu/etd/documentdata.eTD?documentid=4405.

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Thesis (M.S.)--West Virginia University, 2005.<br>Title from document title page. Document formatted into pages; contains xiv, 86 p. : ill. (some col.). Includes abstract. Includes bibliographical references (p. 73-76).
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Young, John Aerospace Civil &amp Mechanical Engineering Australian Defence Force Academy UNSW. "Numerical simulation of the unsteady aerodynamics of flapping airfoils." Awarded by:University of New South Wales - Australian Defence Force Academy. School of Aerospace, Civil and Mechanical Engineering, 2005. http://handle.unsw.edu.au/1959.4/38656.

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There is currently a great deal of interest within the aviation community in the design of small, slow-flying but manoeuvrable uninhabited vehicles for reconnaissance, surveillance, and search and rescue operations in urban environments. Inspired by observation of birds, insects, fish and cetaceans, flapping wings are being actively studied in the hope that they may provide greater propulsive efficiencies than propellers and rotors at low Reynolds numbers for such Micro-Air Vehicles (MAVs). Researchers have posited the Strouhal number (combining flapping frequency, amplitude and forward speed)
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Wabick, Kevin. "Leading-edge vortex development on a maneuvering wing in a uniform flow." Diss., University of Iowa, 2019. https://ir.uiowa.edu/etd/6873.

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Vortices interacting with the solid surface of aerodynamic bodies are prevalent across a broad range of geometries and applications, such as dynamic stall on wind turbine and helicopter rotors, the separated flows over flapping wings of insects, birds, formation of the vortex wakes of bluff bodies, and the lift-producing vortices formed by aircraft leading-edge extensions and delta wings. This study provides fundamental insights into the formation and evolution of such vortices by considering the leading-edge vortices formed in variations of a canonical flapping wing problem. Specifically, the
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Koyama, Ye-Bonne. "Characterisation and aerodynamic impact of leading-edge vortices on propeller blades." Thesis, Université Paris-Saclay (ComUE), 2018. http://www.theses.fr/2018SACLX021/document.

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Cette thèse concerne l’aérodynamique de pales d'extrémité transsonique. Ces pales sont conçues pour maximiser le rendement en croisière, tout en générant la traction requise au décollage. Elles ont des profils fins et peu cambrés, travaillant à forte incidence au décollage, ce qui peut entraîner l’apparition d’un tourbillon de bord d’attaque (TBA). Or ce TBA présente des similitudes avec les tourbillons d’apex d’aile Delta, connus pour leur capacité à générer de la portance tourbillonnaire.Cette étude consiste à examiner l’intérêt du TBA pour les performances aérodynamiques.La démarche a consi
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Berdon, Randall. "Flow structures and aerodynamic loads of a rolling wing in a free stream." Thesis, University of Iowa, 2019. https://ir.uiowa.edu/etd/6705.

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The leading-edge vortex (LEV) is a structure found in unsteady aerodynamics that can alter the forces induced on wings and other rotating structures. This thesis presents an experimental study on LEV development on low aspect-ratio wing rolling in a uniform flow at high angles of attack. The flow structure dynamics of rotating wings in the presence of a free stream are not well understood due to the limited studies under these conditions. In this study, a broad parameter space with varying advance ratio and wing radius of gyration are analyzed using dye-visualizations. In most cases, either a
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Schaeffler, Norman Walter. "All The King's Horses: The Delta Wing Leading-Edge Vortex System Undergoing Vortex Breakdown: A Contribution to its characterization and Control under Dynamic Conditions." Diss., Virginia Tech, 1998. http://hdl.handle.net/10919/30454.

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The quality of the flow over a 75 degree-sweep delta wing was documented for steady angles of attack and during dynamic maneuvers with and without the use of two control surfaces. The three-dimensional velocity field over a delta wing at a steady angle of attack of 38 degrees and Reynolds number of 72,000 was mapped out using laser-Doppler velocimetry over one side of the wing. The three-dimensional streamline and vortex line distributions were visualized. Isosurfaces of vorticity, planar distributions of helicity and all three vorticity components, and the indicator of the stability of the co
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Gunasekaran, Sidaard. "Relationship Between the Free Shear Layer, the Wingtip Vortex and Aerodynamic Efficiency." University of Dayton / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1470231642.

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Frank, Spencer. "Vortex tilting and the enhancement of spanwise flow in flapping wing flight." Honors in the Major Thesis, University of Central Florida, 2011. http://digital.library.ucf.edu/cdm/ref/collection/ETH/id/384.

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In summary the tilting mechanism helps to explain the overall flow structure and the stability of the leading edge vortex.; The leading edge vortex has been identified as the most critical flow structure for producing lift in flapping wing flight. Its stability depends on the transport of the entrained vorticity into the wake via spanwise flow. This study proposes a hypothesis for the generation and enhancement of spanwise flow based on the chordwise vorticity that results from the tilting of the leading edge vortex and trailing edge vortex. We investigate this phenomenon using dynamically sca
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Jaouani, Nassim. "Modelling of installation effects on the tonal noise radiated by counter-rotating open rotors." Thesis, Lyon, 2017. http://www.theses.fr/2017LYSEC002.

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The Counter-Rotating Open Rotors (CROR) are identified as a possible alternative to turbofan engines for middle-range aircrafts. Providing significant fuel savings and reducing the green-house gas emissions, they may lead however to an increased noise radiation due to the absence of nacelle shielding. To properly predict the acoustic radiation of such systems is then mandatory both to reduce the source mechanisms of the isolated engine and to offer an optimal noise installation solution. Such an objective is tackled in the present thesis in two steps. In a first part, the research aims at pred
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Nabawy, Mostafa. "Design of insect-scale flapping wing vehicles." Thesis, University of Manchester, 2015. https://www.research.manchester.ac.uk/portal/en/theses/design-of-insectscale-flapping-wing-vehicles(5720b8af-a755-4c54-beb6-ba6ef1a13168).html.

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This thesis contributes to the state of the art in integrated design of insect-scale piezoelectric actuated flapping wing vehicles through the development of novel theoretical models for flapping wing aerodynamics and piezoelectric actuator dynamics, and integration of these models into a closed form design process. A comprehensive literature review of available engineered designs of miniature rotary and flapping wing vehicles is provided. A novel taxonomy based on wing and actuator kinematics is proposed as an effective means of classifying the large variation of vehicle configurations curren
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Livres sur le sujet "Vortex-motion. Leading edges (Aerodynamics)"

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Kogan, M. N. Receptivity of flat-plate boundary layer in a non-uniform free stream (vorticity normal to the plate): Under cooperative agreement NCC1-241. National Aeronautics and Space Administration, Langley Research Center, 1997.

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Kogan, M. N. Receptivity of flat-plate boundary layer in a non-uniform free stream (vorticity normal to the plate): Under cooperative agreement NCC1-241. National Aeronautics and Space Administration, Langley Research Center, 1997.

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Kogan, M. N. Receptivity of flat-plate boundary layer in a non-uniform free stream (vorticity normal to the plate). National Aeronautics and Space Administration, Langley Research Center, 1997.

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Kogan, M. N. Receptivity of flat-plate boundary layer in a non-uniform free stream (vorticity normal to the plate): Under cooperative agreement NCC1-241. National Aeronautics and Space Administration, Langley Research Center, 1997.

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Terry, Ng T., Nelson Robert C. 1942-, United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., University of Notre Dame. Dept. of Aerospace and Mechanical Engineering., and Ames Research Center, eds. Visualization of leading edge vortices on a series of flat plate delta wings. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1991.

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United States. National Aeronautics and Space Administration., ed. An experimental analysis of critical factors involved in the breakdown process of leading edge vortex flows. Aerodynamics Laboratory, Dept. of Aerospace and Mechanical Engineering, University of Notre Dame, 1991.

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E, Reubush David, Haddad Raymond C, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program, eds. Flow field over the wing of a delta-wing fighter model with vortex control devices at Mach 0.6 to 1.2. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

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E, Reubush David, Haddad Raymond C, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. Flow field over the wing of a delta-wing fighter model with vortex control devices at Mach 0.6 to 1.2. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

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Leading edge vortex dynamics on a pitching delta wing: A thesis. Dept. of Aerospace and Mechanical Engineering, University of Notre Dame, 1990.

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E, Byrd James, Wesselmann Gary F, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. Influence of airfoil geometry on delta wing leading-edge vortices and vortex-induced aerodynamics at supersonic speeds. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

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Chapitres de livres sur le sujet "Vortex-motion. Leading edges (Aerodynamics)"

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Yehia Zakaria, Mohamed. "Unsteady Aerodynamics of Highly Maneuvering Flyers." In Biomimetics. IntechOpen, 2021. http://dx.doi.org/10.5772/intechopen.94231.

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In this chapter, a set of analytical aerodynamic models, based on potential flow, that can be used to predict the unsteady lift response during pitching maneuvers are presented and assessed. The result examines the unsteady lift coefficients experienced by a flat plate in high-amplitude pitch ramp motion. The pitch ramps are chosen based on two ramp pitch maneuvers of a maximum amplitudes of 25 and 45 degrees starting from zero degree. The aim is investigate the use of such classical models in predicting the lift dynamics compared to a full physical-based model. Among all classical methods used, the unsteady vortex lattice method (without considering the leading edge vortex) is found to be a very good predictor of the motion lift dynamic response for the 25 ° ramp angle case. However, at high pitch maneuvers (i.e.,the 45 ° ramp angle case), could preserve the response pattern with attenuated amplitudes without high computational burden. These mathematical analytical models presented in this chapter can be used to obtain a fast estimate for aircraft unsteady lift during pitch maneuvers instead of high fidelity models, especially in the early design phases.
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Cantor, Brian. "The Burgers Vector." In The Equations of Materials. Oxford University Press, 2020. http://dx.doi.org/10.1093/oso/9780198851875.003.0011.

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When a material is stretched beyond its elastic limit, the atoms and molecules begin to slide over each other. This is called plasticity, and is dominated by the motion of defects in the crystal structure of the material, notably line defects called dislocations. The structure and magnitude of a dislocation is defined by its Burgers vector, which is a topological constant for a given dislocation line in a given material, so there is an effective Burgers equation: b = constant. This chapter describes: the structure of edge; screw and mixed dislocations and their associated line energy; the way in which dislocations are generated and interact under stress, leading to the yield point, work hardening and a permanent set in the material; and the use during manufacturing of deformation processing, annealing, recovery and recrystallisation. Jan Burgers’ early life in Arnhem at the beginning of the 20th century is described, as are: his time as a student with the charismatic but depressive Paul Ehrenfest, who later committed suicide; his appointment as the first Professor of Aerodynamics at Technische Universiteit Delft at a time of massive growth in the aviation industry; his contributions to aerodynamic and hydrodynamic flow as well as major Dutch engineering projects such as the Zuiderzee dams and the Maas river tunnel; his growing disaffection with the commercialisation of science and its use in warfare; and his philosophical dalliance with Soviet communism and then American capitalism.
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Actes de conférences sur le sujet "Vortex-motion. Leading edges (Aerodynamics)"

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Lozano, Rafael, Vrishank Raghav, and Narayanan Komerath. "Aerodynamics of a Yawed Blade in Reverse Flow." In ASME 2012 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/imece2012-85947.

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The retreating blades of rotorcraft operated at high advance ratios will experience reverse flow through a sector encompassing a wide range of blade azimuth angles. There is a great deal of uncertainty in the blade aerodynamic loads under these conditions. This is a limiting factor when trying to improve the flight speed envelope of helicopters. Previous studies and work have used two-dimensional aerodynamic approaches for the reverse flow area, making the assumption that aerodynamic forces behave similar in magnitude but opposite in direction. There have been no 3-dimensional considerations b
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Hart, Adam, and Lawrence Ukeiley. "Unsteady Aerodynamics on a Low Aspect Ratio Flat Plate." In ASME 2010 3rd Joint US-European Fluids Engineering Summer Meeting collocated with 8th International Conference on Nanochannels, Microchannels, and Minichannels. ASMEDC, 2010. http://dx.doi.org/10.1115/fedsm-icnmm2010-30846.

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The study of biological flight has shown the potential of using unsteady fluid mechanism to enhance lift and drag capabilities in low Reynolds number flight regimes. To help further the knowledge of unsteady aerodynamic fluid phenomena, a low aspect ratio flat plate is subjected to a pitching motion superimposed on a plunging motion. Variations in this motion are introduced by adding a phase lag to the pitching cycle relative to the plunge cycle. Particle Image Velocimetery (PIV) is used to measure the instantaneous velocity fields over the upper surface of the flat plate at several points in
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Yin, Bo, and Guowei Yang. "Investigation of Obstacle Effects on the Aerodynamic Performance of Flapping Wings." In ASME 2017 Fluids Engineering Division Summer Meeting. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/fedsm2017-69264.

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The study of highly unsteady wing flapping includes the large scale vortices, complicated locomotion/dynamics and deformable wing structures. When flapping insects/birds approach or perch on some objects, such as ground, wall or obstacle, the solid boundary dissipates, absorbs and bounces the leading edge, trailing edge and wing tip vortices, which are generated and shed during the flapping flight. Such phenomenon creates a high pressure area, leads to cushion effect and influences the aerodynamics, stability and maneuverability significantly. This paper uses immersed boundary method (IBM) to
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REYNOLDS, G. A., and A. A. ABTAHI. "Instabilities in Leading-Edge Vortex Development." In 5th Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-2424.

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Mitchell, Anthony, Pascal Molton, Didier Barberis, and Jean Delery. "Control of leading-edge vortex breakdown by trailing edge injection." In 17th Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-3202.

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LEMAY, S., S. BATILL, and R. NELSON. "Leading edge vortex dynamics on a pitching delta wing." In 6th Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-2559.

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Limacher, Eric J., and David E. Rival. "On the Stable Leading Edge Vortex in Rotating Systems." In 32nd AIAA Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-2700.

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Huang, X., Y. Sun, E. Hanff, X. Huang, Y. Sun, and E. Hanff. "Further investigations of leading-edge vortex breakdown over delta wings." In 15th Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-2263.

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O'NEIL, P., R. BARNETT, and C. LOUIE. "Numerical simulation of leading-edge vortex breakdown using an Eulercode." In 7th Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2189.

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van Noordenburg, M., and H. Hoejmakers. "Compressible inviscid flow solutions for isolated leading-edge vortex cores." In 16th AIAA Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-2528.

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