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http://dx.doi.org/10.20910/JASE.2019.13.5.32

Computational Fluid Dynamics of the aerodynamic characteristics for Flying Wing configuration with Flaperon  

Ko, Arim (ULV and LSA Certification Team, UAS Safety Division, Korea Institute of Aviation Safety Technology)
Chang, Kyoungsik (School of Mechanical Engineering, Ulsan University)
Park, Changhwan (Department of Aeronautical & Mechanical Engineering, Hanseo University)
Sheen, Dongjin (Department of Aeronautical & Mechanical Engineering, Hanseo University)
Publication Information
Journal of Aerospace System Engineering / v.13, no.5, 2019 , pp. 32-38 More about this Journal
Abstract
The flying wing configuration with high sweep angles and rounded leading edge represent a complex flow of structures by the leading edge vortex. For control of the tailless flying wing configuration with unstable directional stability, flaperon is used. In this study, we conducted numerical simulations for a non-slender flying wing configuration with a rounded leading edge and analyzed the effect of the sideslip angle and flaperon. Through aerodynamic coefficient analysis, it was found that the effect of AoS on lift and drag coefficient was minimal and the side force and moment coefficient were markedly influenced by AoS. As the sideslip angle increased, the pitch break, which is related to the pitching moment coefficient, was delayed. Through stability analysis, the directional and lateral static stability of the flying wing configuration were increased by flaperon. Also, the structure and behavior of the leading edge vortex were analyzed by observing the contour of the pressure coefficient and the skin friction line.
Keywords
Flying wing; Delta wing; Flaperon; Leading Edge Vortex; Static stability;
Citations & Related Records
Times Cited By KSCI : 2  (Citation Analysis)
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