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.
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。
The model USES the curved vortex elements on the circular arc as the basic discrete elements for trailed filaments and utilizes the free wake extension to form an adaptive far wake downstream.
该模型采用圆弧涡元作为基本涡元，并依据自由尾迹涡线确定远尾迹形状以使远尾迹更接近实际和自由。
A free wake analytical model is then developed for predicting the aerodynamic characteristics of a scissors tail rotor and validated by numerical examples.
然后，建立了一个剪刀式尾桨气动特性计算的分析模型，并进行了验证。
Based on the vortex theory, lifting surface method is used to establish wind turbine performance prediction model with rigid cylinder wake model, prescribed wake model and free-wake method.
采用基于涡系理论的模型建立刚性圆柱尾迹和预定尾迹模型的升力面法预测程序，对无偏航情况的风力机性能进行了预测。
Based on the rotor free-wake model and the rotor trim model, an analytical method is developed for the prediction of helicopter rotor induced velocities on missile trajectory.
应用自由尾迹方法和旋翼配平模型，建立了一个悬停和前飞状态旋翼在导弹发射线上的诱导速度计算模型。
The vortex wake and its induced velocity of a helicopter rotor operating near the ground at low forward speeds have been studied using a simplified free wake-ground vortex model.
本文用一简化自由涡模型模拟旋翼尾涡系，用一简单涡模拟地面涡，对近地低速飞行时旋翼尾涡系的畸变及其引起的诱导速度变化作了研究。
A computational method based on rotor free-wake model was developed for horizontal axis wind turbine's aerodynamic performance prediction.
转子自由尾迹模型的基础上开发的计算方法为水平轴风力发电机的空气动力性能的预测。
In Chapter 3, based upon the blade second-order lifting-line model and rotor free-wake model, an analytical method is developed for predicting the rotor wake structure and BVI airload.
基于桨叶二阶升力线理论和旋翼自由尾迹模型，本文在第三章建立了一个适合于直升机旋翼尾迹结构及桨-涡干扰气动特性分析的方法和模型。
The effect of helicopter fuselage on its rotor is studied using a simplified free-wake model.
本文用简化的自由涡模型研究旋翼近场尾涡系在机身影响下的畸变及其产生的诱导速度交化。
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.
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。
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