尖顶弯折三角翼气动特性研究  

EXPERIMENTAL INVESTIGATIONON THE AERODYNAMICCHARACTERISTICS OFDELTA-WINGS WITH APEX FLAP

作　　者：展京霞[1] 徐 燕[1] 王晋军[1] 

机构地区：[1]北京航空航天大学飞行器设计与应用力学系,北京100083

出　　处：《力学与实践》2002年第3期12-15,共4页Mechanics in Engineering

基　　金：国防科技预先研究基金资助.

摘　　要：对75°后掠三角翼在40%根弦处弯折引起的升阻特性及俯仰特性的变化进行了低速风洞实验研究,初步分析了尖顶弯折对三角翼气动特性的影响趋势．得出尖顶弯折在低速大攻角下,可以使升力系数Cy增大、升阻比提高,并推迟失速攻角αmax,从而说明顶部弯折对三角翼气动特性的改善作用是显著的．The variations of the lift coefficient,drag coefficient and pitch moment due to the apexflap located at 40 percent of the root chord of adelta-wing are investigated in the low-speed windtunnel. The experiment indicates the influence ofthe apex flap. It is shown that the apex flap canenhance the lift coefficient, lift-drag ratio and stallangle of attack. Thus, it can be concluded thatthe apex flap may greatly improve the aerodynamiccharacteristics of a delta-wing.

关 键 词：三角翼 尖顶弯折角 风洞实验 升力系数 升阻比 气动特性 

分 类 号：V212.11[航空宇航科学与技术—航空宇航推进理论与工程] V214.11