翼尖涡沿着展向方向向外移动，机翼诱导阻力减小。
Tip vortex goes downstream outward along the span direction, and the induced drag of the wing decreases.
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；
Image method ideal vortex model is used for the analysis of how ground effect impacts wingtip vortex and airflow downwash angle.
试验采用简化的飞机模型(有尾翼)，建立了包含一对翼尖涡及一对反向旋转的尾翼涡(通过以负迎角安装尾翼得到)的4涡尾流系统。
In the experiment, a simplified aircraft model (with tail wing) is employed to construct a 4-vortex wake system consisting of a pair of tip vortices and a pair of counter rotating tail plane vortices.
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。
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.
首先从预定的广义尾流入手，并引入尖涡涡核作用的半经验修正，对旋翼的自由尾流进行计算分析。
Beginning with the prescribed wake model, a Semi Empirical Correction for the vortex core effect on rotor wake is made and free wake calculation is carried out.
建立了一个旋翼桨尖涡初始涡核半径计算模型，用于消除旋翼自由尾迹分析中桨尖涡涡核半径依靠经验设定的现状。
A model is developed for the calculation of the initial rotor tip vortex core radius aiming at eliminating the empirical parameters of the tip vortex in rotor free-vortex wake analysis.
建立了一个旋翼桨尖涡初始涡核半径计算模型，用于消除旋翼自由尾迹分析中桨尖涡涡核半径依靠经验设定的现状。
A model is developed for the calculation of the initial rotor tip vortex core radius aiming at eliminating the empirical parameters of the tip vortex in rotor free-vortex wake analysis.
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