The second part studies and analyzes the tip leakage flow and tip vortex.
第二部分对叶顶间隙泄漏流动和叶尖涡进行了研究分析。
Tip vortex goes downstream outward along the span direction, and the induced drag of the wing decreases.
翼尖涡沿着展向方向向外移动，机翼诱导阻力减小。
The analytical method for predicting the hovering rotor wake is described to investigate the motion of the helical tip vortex.
用文中描述的尾流分析方法研究了螺旋尖涡的运动。
The effect of the sawtooth shape tip on tip vortex of the propeller is studied with the theory of vortex dynamics in the paper.
本文用涡动力学理论分析了锯齿形叶梢对螺旋桨的梢涡的影响。
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。
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。
The wake is mixing with the last rotor tip leakage vortex in the stator passage, leading to more substantial fluctuations in the flow field.
转子尾迹在静子通道内追赶上从前一转子叶片通道内下来的叶尖泄漏涡，二者的相互作用和掺混导致静子尖区更为复杂的二次流动。
The rotor tip leakage vortex has a stronger influence on the downstream endwall flow than the rotor wake.
同转子尾迹相比，转子叶尖泄漏涡对静子尖区的影响更为明显和深远。
The tip leakage vortex may have greater effect than other vortexes, that is consistent with the experimental results.
不同二次流与叶片颤振的相关性中尖部漏流涡对叶片气弹稳定性的影响较大。
The results showed that the main flow rolled up the leakage flow of the tip clearance and generated the tip leakage vortex.
结果表明：叶顶间隙气流与主流发生卷吸而生成泄漏涡。
The results show that the tip leakage flow vortex has a great effect on the blade aeroelastical stability and large tip leakage vorticity may restrain blade flutter.
计算结果表明，漏流涡对叶片气弹稳定性影响较大，大涡量的漏流涡能抑制叶片颤振发生。
Suppressed by the up passage vortex at upstream side of blade, the intensity and scale of the tip clearance leakage vortex is decreased.
渐缩型间隙在叶片前半轴弦受到上通道涡的抑制，减少了叶顶间隙泄漏涡的强度和范围；
The velocity vector and vortical contour in three different circumference positions were successfully acquired and the structure of the tip leakage vortex was clearly illustrated.
测量得到了三个不同周向位置下的涡量图和速度矢量图，并观测到了叶顶泄漏涡的涡旋结构。
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.
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.
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。
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