Lift Enhancement of Delta Wing with a Hybrid Method of Leading Edge Rotation and Trailing Edge Jet
نویسندگان
چکیده
منابع مشابه
Morphing Trailing Edge Flap for High Lift Wing
This paper presents the study conducted to design and analyze a morphing trailing edge flap structure for a large aircraft wing. The rear part of the trailing edge flap was modified to be integrated with a set of internal actuation mechanisms distributed along the span of the flap. Additional changes to the conventional flap structure were implemented, such as an open sliding trailing edge and ...
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Recent investigations on the aerodynamics of natural fliers have illuminated the significance of the leading-edge vortex (LEV) for lift generation in a variety of flight conditions. A well-documented example of an LEV is that generated by aircraft with highly swept, delta-shaped wings. While the wing aerodynamics of a manoeuvring aircraft, a bird gliding and a bird in flapping flight vary signi...
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Nhan T. Nguyen a NASA Ames Research Center, Moffett Field, CA 94035 Nathan Precup b and Eli Livne c University of Washington, Seattle, WA 98195 James Urnes, Sr. d Boeing Research & Technology, St. Louis, MO 63134 Eric Dickey e Boeing Research & Technology, Huntington Beach, CA Chester Nelson f Boeing Commercial Airplanes, WA 98124 Jonathan Chiew g Stanford University, Stanford, CA 94305 David L...
متن کاملControl System Design for a Morphing Wing Trailing Edge
Shape control of adaptive wings has the potential to enhance wing aerodynamic performance during cruise and high-speed off-design conditions. A possible way to attain this objective is to develop specific technologies for trailing edge morphing, aimed at variating the airfoil camber. In the framework of SARISTU project (EU-FP7), an innovative structural system incorporating a gapless deformable...
متن کاملComputation of Trailing Edge Noise with a Discontinuous Galerkin Method
Trailing edge noise of a semi-infinite, thin, flat plate situated in low Mach number flow is computed in two spatial dimensions. The Acoustic Perturbation Equations (APE), which are employed as governing equations, are discretized via a Discontinuous Galerkin Method (DGM). Results are compared with theory and Finite Difference (FD) computations. Next to the radiated sound field, special attenti...
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ژورنال
عنوان ژورنال: JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
سال: 2006
ISSN: 1344-6460
DOI: 10.2322/jjsass.54.116