民用飞机增升构型前缘下垂参数影响分析  

Effect of droop nose devices design parameters on lift characteristics for civil aircraft

作　　者：罗佳茗 刘苍松 王祁旻 虞佳磊 马涂亮[1] LUO Jiaming;LIU Cangsong;WANG Qimin;YU Jialei;MA Tuliang(Shanghai Aircraft Design and Research Institute,Shanghai 201210,China)

机构地区：[1]上海飞机设计研究院,上海201210

出　　处：《民用飞机设计与研究》2022年第3期41-46,共6页Civil Aircraft Design & Research

摘　　要：采用计算流体力学方法,针对基于典型二维多段翼型NACA0410设计的带前缘下垂构型的多段翼型进行数值模拟,研究了前缘下垂四种参数对多段翼升力特性的影响。在所研究的范围内,结果表明:1)在线性段,弦长增加与偏度增大对线性升力均有负面影响,但转轴高度与尾缘夹角对线性升力几乎没有影响;2)在近失速及失速段,弦长增加与尾缘夹角的提升,可明显提升升力;下垂偏度增加,以26°为界,小于该角度可提升升力,但大于该角度后,影响不再明显;随转轴高度下降,升力出现一定提升,但到2 mm后反而有所下降;前缘下垂尾缘夹角增大,可提升近失速段升力;3)四参数对升力影响主要体现在头部两段吸力峰的消长,设计中需综合考虑吸力峰特征,并加以应用。In this paper, the computational fluid dynamic method was applied to simulate the flow field around 2 D multi-element airfoil with droop nose devices(DND) at leading edge. A typical 2 D airfoil NACA0410 was used to design the multi-element airfoil. The effect of four factors used to design DND on aerodynamic characteristics of a multi-element airfoil was studied. The result shows that, 1) in the linear segment, increases in chord length and deflection angle both have negative effect on lift, but the angle between the hinge height and the trailing edge has little effect on lift;2) close to/at stalling point, increases in chord length and trailing edge angle can obviously increase lift;lift increases when deflection angle is less than 26° and lift increases as hinge height decreases, but decreases when hinge height is less than 2 mm;3) 4 parameters mainly affect the fluctuation of two suction peaks at the leading edge. These four parameters should be comprehensively considered and applied during design.

关 键 词：前缘下垂(DND) 升力 民用飞机 气动设计 增升装置设计 计算流体力学 

分 类 号：V224.5[航空宇航科学与技术—飞行器设计]