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.
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.
用文中描述的尾流分析方法研究了螺旋尖涡的运动。
The analytical method for predicting the hovering rotor wake is described to investigate the motion of the helical tip vortex.
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