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Leading-edge flow sensing for detection of vortex shedding from airfoils in unsteady flows
The Physics of Fluids, 2021Sensing of vortex shedding in unsteady airfoil flows can be beneficial in controlling and positively harnessing their effects for increased aerodynamic performance.
Aditya Saini +2 more
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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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Radial planetary vorticity tilting in the leading-edge vortex of revolving wings
The Physics of Fluids, 2019Previous studies suggested that Coriolis acceleration and spanwise flow both played key roles in stabilizing the leading-edge vortex (LEV) in revolving wings.
Nathaniel H. Werner +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 Interactions at a Generic Multiple Swept-Wing Aircraft Configuration
Journal of Aircraft, 2019Experimental investigations on a generic low-aspect-ratio aircraft configuration with triple and double delta wing planforms were performed at subsonic speed.
S. Pfnür, C. Breitsamter
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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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Vortex separation above delta leading edges.
Journal of Aircraft, 1967and that the jet flow would attach at the inlet lip. The inspections of Fig. 4 shows that the round lip, created by the jet flow, extended well inside the inlet lip and restricted the inlet flow area. Thus, the pressure recovery improvements that might have been realized as the result of rounding the lip were offset by higher pressure losses associated
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The compressible inviscid leading-edge vortex
Journal of Fluid Mechanics, 1965The conically symmetric solution of the Eulerian equations of an incompressible fluid obtained by Hall, thought to be descriptive of flow properties in a leading-edge vortex, is generalized to include the effects of compressibility.
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