Analysis of a 3D Unsteady Morphing Wing with Seamless Side-edge Transition 机翻标题: 暂无翻译,请尝试点击翻译按钮。

会议集名/来源
36th AIAA applied aerodynamics conference 2018, vol. 2: 36th AIAA applied aerodynamics conference held at the AIAA aviation forum 2018, 25-29 June 2018, Atlanta, Georgia, USA
出版年
2018
页码
1099-1112
会议地点
Atlanta
作者单位
Department of Engineering Design and Mathematics, University of the West of England, Coldharbour Lane, Frenchay, Bristol BS16 1QY, United KingdomDepartment of Engineering Design and Mathematics, University of the West of England, Coldharbour Lane, Frenchay, Bristol BS16 1QY, United KingdomDepartment of Engineering Design and Mathematics, University of the West of England, Coldharbour Lane, Frenchay, Bristol BS16 1QY, United KingdomDepartment of Engineering Design and Mathematics, University of the West of England, Coldharbour Lane, Frenchay, Bristol BS16 1QY, United Kingdom
作者
Chawki Abdessemed;Yufeng Yao;Abdessalem Bouferrouk;Pritesh Narayan
摘要
In this paper, a comparative study between a NACA 0012 rectangular wing with a statically morphed Trailing Edge Flap (TEF) and the same wing with a hinged flap is performed at a Reynolds number based on the chord length of Re = 0.62×10~6 and a Mach number of 0.115. Furthermore, an unsteady flow analysis of a dynamically morphing wing is performed, taking care to model the flap side-edge between the morphing and static parts. The deformation is parametrized in time for the morphing TEF portion and a parametrization for the transition is introduced to eliminate the flap side-edge gap and model its deformation as a seamless surface. Dynamic meshing methods were used to deform the computational grid and accurately capture the aerodynamic features of the unsteady morphing wing. The modified parametrization method was implemented successfully and an analysis of the unsteady morphing effects was carried out. The Shear Stress Transport (SST) model was utilized to model turbulence in all studied configurations whose performances were evaluated for a range of angles of attack. It was found that at low Angles of Attack the morphing TEF with the seamless transition displays an increased aerodynamic efficiency compared with the hinged flap configuration, yet the performance of the morphed TEF deteriorates at higher AoA while the hinged flap wing performs consistently. Finally, this paper introduces a framework to model accurately a 3D morphing wing with a seamless transition using an unsteady parametrization method and dynamic meshing. The unsteady analysis of the dynamically morphed wing has shown that the TEF motion induces complex flow phenomena, paving the way for in-depth high fidelity analysis using the developed framework.
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