摘要
介绍了三种翼梢减阻装置：后掠翼梢、分段后掠机翼和下弯翼梢。重点给出改变后掠翼梢的几何参数对减阻效果的影响。风洞实验表明，经优化设计的后掠翼梢可使诱导效率ｅ提高４％～７％。后掠翼梢使飞机纵向静稳定性增大。水洞实验表明，后掠翼梢减阻的原因主要是在有迎角时，翼梢前缘涡和后缘涡共问作用削弱了翼梢涡，从而减小了飞机的诱导阻力。
hree kinds of devices of drag reducing are presented:swept wing-tip,stage by stage swept wing and downbend wing-tip. The effcets of changing geometry parameters of the swept wing-tip on the drag reducing are also presented.Wind-tunnel experiment results indicate that a properly designed swept wing-tip results in an increment in indueed efficiency of 4%～7% nd that swept wing-tip can increase longitudinal static-stability.Water-tunnel experiment re- sults indicate that the reason for drag reducing of swept wing-tip is that when the angle of attack is not Zero,the strength tip vortex of the wing is weakened by the combined effect of the leading edge and trailing edge vortices of the swept wing-tip.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1994年第8期897-903,共7页
Acta Aeronautica et Astronautica Sinica
关键词
机翼
风洞试验
减阻
轻型飞机
light aircraft,drag reduction, wind tunnel tests
