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跨音速机翼采用鼓包主动减阻技术研究
引用本文:杨洋、陈迎春、黄炜.跨音速机翼采用鼓包主动减阻技术研究[J].民用飞机设计与研究,2012(2):13-17,61.
作者姓名:杨洋、陈迎春、黄炜
作者单位:上海飞机设计研究院,上海200232
摘    要:对二维、三维鼓包进行激波控制减阻,并在大型客机的机翼上进行了对比研究。在研究鼓包减阻的机理时,采用了超临界翼型,鼓包的几何形状及鼓包位置的优化也进行了研究。研究结果表明,鼓包位置、形状及串列式分布对机翼的减阻影响较大。最后把得到的研究结果应用到大型飞机的激波减阻上,结果表明,该方法能较大程度地减小激波阻力,进而提高飞机的升阻比,提高飞机的气动效率。

关 键 词:鼓包控制激波  跨音速  超临界机翼  减阻

Active Drag-Reducing Technique Using Bumps on Transonic Wings
Yang Yang,Chen Yingchun,Huang Wei.Active Drag-Reducing Technique Using Bumps on Transonic Wings[J].Civil Aircraft Design and Research,2012(2):13-17,61.
Authors:Yang Yang  Chen Yingchun  Huang Wei
Institution:Yang Yang Chen Yingchun Huang Wei(Shanghai Aircraft Design Research Institute,Shanghai 200232,China)
Abstract:Research on shock wave drag-reducing using two dimensional and three dimensional bumps is performed, including comparisons on wings of large aircraft. The mechanism of bump drag-reducing is researched via supercritical airfoil profile, and geometrical shape and location of bump are optimized. The research results show that location, shape and serial distribution of bump have significant effects on drag-reducing for wings. Finally, the drag-reducing technique using bumps is applied to the large aircraft. As a result, the presented technique reduces shock wave drag to a great extent, increases the ratio of lift to drag, and improves aerodynamic efficiency of the aircraft.
Keywords:Bump Controlling Shock Wave  Transonic  Supercritical Wing  Drag-Reducing
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