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Fuzzy control of wing rock for slender delta wings
TENCON'92 - Technology Enabling Tomorrow, 1993Fuzzy logic-based roll controllers are designed to control wing-rock motion of a free-to-roll stinged delta wing. The dynamics of an aircraft is a complex function of flight conditions. The free-to-roll stinged delta wing permits investigation of these variations, as well as the highly nonlinear dynamics of limit cycle at high angle-of-attack.
J. H. Tarn, F. Y. Hsu
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AIAA Journal, 1985
Delta wings in steady flow can provide high lift at large angles of attack and are therefore used on many highperformance aircrafts. However, the unsteady aerodynamic properties of a delta wing are practically unknown, although vital for operating and designing airplanes for poststall and other maneuvering.
Mohamed Gad-el-Hak, Chih-Ming Ho
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Delta wings in steady flow can provide high lift at large angles of attack and are therefore used on many highperformance aircrafts. However, the unsteady aerodynamic properties of a delta wing are practically unknown, although vital for operating and designing airplanes for poststall and other maneuvering.
Mohamed Gad-el-Hak, Chih-Ming Ho
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Wing Rock of Nonslender Delta Wings
Journal of Aircraft, 2000That slender delta wings will experience wing rock is an established fact, and the responsible flow mechanism is well understood. However, the same flow mechanism could not cause wing rock of nonslender delta wings. Thus, the wing rock observed for a 45-deg delta wing must be generated by a different flow phenomenon.
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Aerodynamical Improvement of Delta Wing and Flapping Wing
Volume 1A: Symposia, Part 2, 2015Recently, various studies of Micro Air Vehicle (MAV) and Unmanned Air Vehicle (UAV) have been reported from wide range points of view. The aim of this study are researching the aerodynamic improvement of delta wing and flapping wing in low Reynold’s number region to develop an applicative these air vehicle.
Tadateru Ishide +5 more
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2006 International Forum on Strategic Technology, 2006
A numerical analysis of free roll vibrations of a delta wing in an ideal incompressible flow (wing rock) is performed by solving the coupled dynamic and unsteady-aerodynamic equations. A computational algorithm is constructed on the basis of the vortex-lattice method.
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A numerical analysis of free roll vibrations of a delta wing in an ideal incompressible flow (wing rock) is performed by solving the coupled dynamic and unsteady-aerodynamic equations. A computational algorithm is constructed on the basis of the vortex-lattice method.
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Self-induced wing rock of slender delta wings
7th Atmospheric Flight Mechanics Conference, 1981As part of a research program aimed at exploring basic mechanisms that cause wing rock in combat aircraft, an investigation was conducted to study the aerodynamic factors which cause the low-speed wing rock exhibited by slender delta wings. A flat-plate delta wing with 80 deg leading-edge sweep was subjected to conventional static-force tests and ...
L. NGUYEN, L. YIP, J. CHAMBERS
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Vortex flow over delta and double-delta wings
Journal of Aircraft, 1983Etude theorique et experimentale de l'ecoulement sur une aile delta et une aile en double ...
H. W. M. Hoeijmakers +2 more
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Flow structure over delta wings
33rd Aerospace Sciences Meeting and Exhibit, 1995High resolution Laser Doppler Anenionictcr (LDA) measurements using a novel technique have rewalcd considerable new detail of the separated vortcs flow OYCI a delta wing. It has been demonstrated that at modest local Reynolds numbers Based on chord (around Re,= 100,000 for an 8 5 O delta wing) the separating shear layer can form into strong, steady ...
Lowson, MV, Riley, AJ, Swales, C
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Applied Mechanics Reviews, 1990
On a delta wing, the separation vorticies can be stationary due to the balance of the vorticity surface flux and the axial convection along the swept leading edge. These stationary vortices keep the wing from losing lift. A highly swept delta wing reaches the maximum lift at an angle of attack of about 40°, which is more than twice as high as that of a
Mario Lee, Chih-Ming Ho
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On a delta wing, the separation vorticies can be stationary due to the balance of the vorticity surface flux and the axial convection along the swept leading edge. These stationary vortices keep the wing from losing lift. A highly swept delta wing reaches the maximum lift at an angle of attack of about 40°, which is more than twice as high as that of a
Mario Lee, Chih-Ming Ho
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2006
A well-known category of flows where Boussinesq’s hypothesis is expected to fail is vortex-dominated flows. Unfortunately, many of the flows of industrial interest involve vortices, such as those emanating from the roof of a car, or from the wing tips of airplanes. The delta wing is another example of a flow where the accurate resolution of the physics
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A well-known category of flows where Boussinesq’s hypothesis is expected to fail is vortex-dominated flows. Unfortunately, many of the flows of industrial interest involve vortices, such as those emanating from the roof of a car, or from the wing tips of airplanes. The delta wing is another example of a flow where the accurate resolution of the physics
openaire +1 more source