| 高空长航时无人机高升阻比两段翼型设计研究 |
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| 引用本文： | 侯成义,龚志斌,刘城斌,周丽琼.高空长航时无人机高升阻比两段翼型设计研究[J].应用力学学报,2011,28(2). |
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| 作者姓名： | 侯成义 龚志斌 刘城斌 周丽琼 |
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| 作者单位： | 西北工业大学,710072,西安 |
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| 摘 要： | 针对某特定无人机的使用设计要求,在单段翼型设计研究的基础上,尝试了高升阻比低雷诺数两段翼型的设计方法的分析与研究.采用求解椭圆型方程加控制点约束条件的"椭圆-控制点切割法"完成了两段翼型外形的生成,并针对巡航构型的襟翼偏角对缝道参数进行了优化;应用MSES计算分析程序对所设计的两段翼型的气动特性进行了分析评估.计算结果表明:本文所设计的两段翼型的最大升力系数达到2.72,最大升阻比为158.71;与原始单段翼型相比,最大升力系数增大了74.35%,最大升阻比增大了28.64%.
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| 关 键 词： | 高空长航时无人机 高升阻比 两段翼型 翼型设计 翼型优化 |
Investigation of the design methodology for the high lift-to-drag ratio two-element airfoil of the high altitude |
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| Hou Chengyi,Gong Zhibin,Liu Chengbin,Zhou Liqiong.Investigation of the design methodology for the high lift-to-drag ratio two-element airfoil of the high altitude[J].Chinese Journal of Applied Mechanics,2011,28(2). |
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| Authors: | Hou Chengyi Gong Zhibin Liu Chengbin Zhou Liqiong |
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| Institution: | Hou Chengyi1 Gong Zhibin2 Liu Chengbin2 Zhou Liqiong2(Defence Science Technology Academe,Northwestern Polytechnical University,Xi'an 710072,China)1(School of Aeronautics,China)2 |
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| Abstract: | According to the design requirements of a special UAV,the design and analysis of the high lift-to-drag ratio two-element airfoil with low Reynolds number is conducted based upon the earlier studies of the one-element airfoil design.The geometry of the two-element airfoil is generated with ellipse-control points cutting method,the slot parameters for the airfoil with the flap deflection under cruise condition are optimized.The MSES code is used in evaluating the aerodynamic performance of the designed two-el... |
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| Keywords: | high altitude and long endurance high lift-to-drag ratio two-element airfoil airfoil design |
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