Results 161 to 170 of about 92,283 (210)
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Leading-edge vortex stability in insect wings
Physical Review E, 2005An analytical study is presented to determine if the persistency of the leading-edge vortex in an insect wing can be explained as the balance between vorticity generation at the leading edge and advection plus effects of vorticity stretching and tilting by the flow along the wing span.
F O, Minotti, E, Speranza
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Leading-Edge-Vortex Augmentation in Compressible Flow
Journal of Aircraft, 1975Leading-edge-vortex enhancement by blowing has been explored experimentally. Conceptual half-span windtunnel tests were conducted on a wing-body-tail configuration with a cambered and twisted wing with leadingedge flaps. Blowing vortex augmentation is shown to be effective in improving both lift and drag due to lift at high angle of attack for the Mach
R. BRADLEY, P. WHITTEN, W. WRAY
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Control of Leading-Edge Vortex Breakdown by Trailing Edge Injection
Journal of Aircraft, 1999The goal of this research is the control of the vortex breakdown locations over sharp-edged, slender, delta wings at high angles of attack. Water tunnel tests of a 75-deg delta wing examined symmetric and asymmetric trailing-edge jet injection as a method to control and delay the leading-edge vortex breakdown locations. These tests were accomplished at
Anthony Mitchell +3 more
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Simulation of leading-edge vortex flows
Theoretical and Computational Fluid Dynamics, 1990zbMATH Open Web Interface contents unavailable due to conflicting licenses.
Hsu, C.-H., Liu, C. H.
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Modeling of leading edge vortex burst
AIAA Atmospheric Flight Mechanics Conference and Exhibit, 2001The burst of leading edge vortex (LEV) is investigated by a modified quasi-cylindrical approximation (MQCA) for the sub-core of the vortex. By assembling LEV with the MQCA and evaluating the total pressure drop along the sub-core of LEV, a model for predicting the location of LEV burst is proposed.
Haiye Lou, X. Huang
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Dynamic Stall Control by Leading Edge Vortex Generators
Journal of the American Helicopter Society, 2008A new concept of passive dynamic-stall control was developed and tested on an OA209 rotorcraft airfoil during two wind-tunnel test campains in 2004 and 2005. Small vortex generators are mounted at the leading edge of the rotor blade. At low incidence they are located close to the stagnation point and do not impact the flow field.
Mai, Holger +6 more
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A multi‐vortex model of leading‐edge vortex flows
International Journal for Numerical Methods in Fluids, 1983AbstractA multi‐vortex model of the vortex sheets shed from the sharp leading edges of slender wings is considered. The method, which is developed within the framework of slender‐body theory, is designed to deal with those situations in which more than one centre of rotation is formed on the wing, for example on a slender wing with lengthwise camber or
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Leading edge vortex and shear layer instabilities
36th AIAA Aerospace Sciences Meeting and Exhibit, 1998The stability of a leading edge vortex was studied using available flow visualization and velocity data. The development of a vortex can be envisioned to compose of three possible stages. During the initial stage, the shear layer and its associated vorticity immediately downstream from the apex coalesce to form a primary vortex core.
T. Ng, Doug Oliver
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Entrainment effect of a leading-edge vortex
AIAA Journal, 1987Etude experimentale des caracteristiques de l'ecoulement dans un tourbillon de bord d'attaque.
N. G. Verhaagen, A.C.H. Kruisbrink
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Numerical simulation of leading-edge vortex flows
17th Fluid Dynamics, Plasma Dynamics, and Lasers Conference, 1984Steady flowfields describing respectively the distinguished structure for subsonic, sonic, and supersonic leading-edge flow about a thin delta wing at angle of attack in a supersonic freestream are calculated numerically. Solutions of the steady three-dimensional compressible laminar Navier-Stokes equations are obtained by time integration.
Donald P. Rizzetta, Joseph S. Shang
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