1) wingtip vortex
翼尖涡
1.
Analysis of wingtip vortex characteristics in flows around low-aspect-ratio thin wings for micro air vehicles;
微型飞行器小展弦比薄翼流场中的翼尖涡特性分析
2.
Image method ideal vortex model is used for the analysis of how ground effect impacts wingtip vortex and airflow downwash angle.
计算结果给出了地效飞行器气动性能随飞行高度和迎角的变化规律;采用镜像法理想涡模型分析了地面效应对翼尖涡位置和气流下洗角的影响;详细阐明了地面效应对诱导阻力的影响规律。
2) tip vortex
翼尖涡
1.
The effect of tip vortex .
然后针对不同的展弦比、减缩频率及初始攻角,计算了矩形扑翼的非定常气动特性及表面流态和动态压力分布,并分析了翼尖涡对扑翼非定常气动特性的影响。
3) wing tip vortex
翼尖涡
1.
The flow field of the wing tip vortex,which shed from a rectangular wing,is surveyed by a seven holes probe in a low speed wind tunnel.
应用七孔探针空间流场定量测试技术研究了翼尖涡的流动结构,给出了翼尖尾涡在下游两倍弦长距离内的速度和压力场分布随迎角变化的规律。
2.
The development of wing tip vortex with alterations of angle-of-attack and aspect ratio is investigated,it is found that wing tip vo.
然后在此基础上分析了弯度、展弦比等因素对小展弦比薄翼气动力特性的影响以及翼尖涡随攻角、展弦比的变化规律,发现翼尖涡是影响小展弦比薄翼气动力的一个重要因素。
6) winglet
[英]['wiŋlit] [美]['wɪŋlɪt]
翼尖小翼
1.
To match these needs,a bigger wing aspect ratio and winglet are adopted as the improvement measures,hopefully the lift-drag ratio of the modified UAV could be increased.
为延长某无人机的留空时间,加大航程和提高升限,用适当加大机翼展弦比和加装翼尖小翼的办法对原型机的气动特性进行了改进,以期能使该无人机的升阻比有较大提高。
2.
Modification of winglet is adopted to raise the lift-drag ratio of the UAV for extension endurance,for enlarge range and for increase ceiling.
为延长无人机留空时间,加大航程和提高升限,可采用加装翼尖小翼的方法使无人机的升阻比有所提高。
补充资料：变后掠翼飞机(见后掠翼飞机)
变后掠翼飞机(见后掠翼飞机)
swing-wing aircraft
bianhoul位eyi feiii变后掠翼飞机(swing一wing aircran)见后掠翼飞机。
说明：补充资料仅用于学习参考，请勿用于其它任何用途。
参考词条