Morphing wing optimizatior for steady level flight 机翻标题: 暂无翻译,请尝试点击翻译按钮。

来源
Proceedings of the Institution of Mechanical Engineers, Part G. Journal of aerospace engineering
年/卷/期
2017 / 231 / G13
页码
2317-2330
ISSN号
0954-4100
作者单位
Univ Turkish Aeronaut Assoc, Aeronaut Engn Dept, Bahcekapi Mahallesi Okul Sokak 11, Ankara, Turkey;Middle East Tech Univ, Aerosp Engn Dept, Ankara, Turkey;
作者
Korpe, Durmus S.;Ozgen, Serkan;
摘要
This paper presents the basic results of the morphing wing planform optimization of an experimental unmanned air vehicle for minimum drag at steady level flight. The aerodynamic design tool that consists of the three-dimensional panel method, two-dimensional boundary layer solution and generalized reduced gradient method-based optimization is appropriate for fixed wing and morphing wing conceptual and preliminary design. The morphing concept is implemented into the solution with the geometric constraints of the wing planform and the airfoil shape design variables. The drag that is created by other components of the aircraft is calculated according to empirical formulas. Wing drag and aircraft drag comparisons between baseline wing (BASE), optimum fixed wing and morphing wing are discussed with the obtained planform and airfoil shapes.
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关键词/主题词
Morphing wing;panel method;boundary layer flow;optimization;low-speed aerodynamics;conceptual airplane design;
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