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.
出处
《力学与实践》
CSCD
北大核心
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.
