It is shown that the present method can effectively reduce the numerical dissipation of the rotor wake.
计算结果表明，本文方法能够有效地减少旋翼尾迹的数值耗散。
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 interaction effects of rotor wake on fuselage for helicopter were researched with experimental method.
试验研究了直升机机身受旋翼气流干扰时的空气动力特性。
First, free wake analysis was carried out to calculate the rotor wake geometry and the downwash around the engine jet space.
首先应用自由尾流分析技术来计算旋翼尾迹和发动机绕排流空间的洗流速度。
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。
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。
To incorporate the important effects of the rotor wake, the far-field boundary condition derived from the rotor momentum theory and the cyclic boundary condition have been used.
为了充分考虑旋翼尾迹对流场的影响，采用周期性边界条件和由动量理论导出的远场边界条件。
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。
Experimental results show that under the effect of the rotor wake, the dominant frequencies of pressure fluctuations on stator blades are the rotor blade passing frequency (BPF) and its harmonics.
实验结果表明：在转子尾迹的影响下，静子叶片表面的波动频率是转子的尾迹频率及其倍频。
Rotor wake effects are modeled in the form of a correction applied to the angle of attack along the blades. This correction is obtained by computing the local induced downwash with free wake analysis.
旋翼尾流的作用通过自由尾流分析来求解局部的诱导下洗速度以修正翼型攻角。
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。
Moreover, because the intensity of vortex shedding in the wake of the guide vane is too weak, it's frequency has no influence on the vibration characteristics of the low-pressure compressor rotor.
同时由于导流体尾迹内部脱落涡强度太低，其脱落频率也不会对发动机低压转子振动特性产生影响。
The wake flow of stator vanes and the unsteady flow in the passage of rotor blades were solved by using oscillating fluid mechanics theory and parametric polynomial method.
采用参数多项式方法和振荡流体力学理论，求解静子叶片后的尾流场及尾流场作用下转子叶片通道内的非定常流场。
Then on the condition of circulation and wake geometry convergence, the rotor thrust is calculated to satisfy convergence criterion of thrust.
然后在环量收敛与尾迹收敛的条件下，计算拉力以满足拉力收敛准则。
In addition, the wake interaction of upstream blade row and the expansion wave at rotor exit also cause an unsteady force acting on the downstream rotor blade surface.
此外上游静子尾迹以及动叶尾缘出口膨胀波等也是产生转子叶片表面非定常力的因素。
An experimental investigation into the properties of the wake behind a horizontal-axis wind turbine (HAWT) rotor is carried out at model scale, using a single slanted hot-wire probe.
在水平轴风力机模型不同尖速比条件下，利用旋转单斜丝热线在风轮下游进行尾迹流场速度测量。
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 wake geometry feature of helicopter rotor in hovering is visualized by experimental method in this paper and the preceding wake geometry model is updated according to the experimental results.
本文用试验的方法显示了悬停状态旋翼的尾迹几何形状，并以试验结果为依据对现有的尾迹几何模型进行了修正。
To reduce the dynamic stress of rotor blades under the wake of front stator vane, an asymmetry stator mistuned design was conducted.
不对称静子叶片分布非谐设计下，转子所受到的激振力由静子叶片均布情况下的单频率高幅值激振力转变为多频率成分低幅值激振力。
Unsteady flow in the rotor is simulated and contrast between the flow field with wake flow at the inlet and that with uniform one is presented.
对尾迹干扰下的转子非定常流场进行数值模拟，与传统设计定常流动假设下均匀进气的流场对比分析了尾迹干扰的影响。
A rotor discrete free wake geometries and the blade airloads at each instant are presented.
旋翼的尾迹流强烈地影响旋翼桨叶的空气动力分布。
The results show that the rotor near-wake is distorted because of the flow field of the fuselage, resulting in large variation on the induced velocity distribution at the rotor plane.
在机身影响下，旋翼近场尾涡形状发生畸变，从而改变桨盘处的诱导速度分布。
A computational method based on rotor free-wake is developed for predictig flow field between the twin rotors of coaxial helicopters.
在随桨叶旋转的坐标系中，建立了悬停旋翼自由尾迹计算的迭代方法和模型。
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。
The variation of the induced velocity distribution at the rotor plane caused by the fuselage through distorting the rotor near-wake is much larger than that induced by the fuselage directly.
尾涡畸变引起的诱导速度变化比机身直接在桨盘处诱导速度大得多。
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 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。
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。
Considering the process of dynamic influence of eddy flow at every section of blades, based on Equilibrium Wake model, dynamic Wake model simulates the dynamic aerodynamic calculations for the rotor.
动态尾流模型又基于平衡尾流模型，考虑桨叶每个截面处产生的涡流对风轮的动态影响过程，对风轮的气动计算进行动态模拟仿真。
Considering the wake influence of blades, based on steady aerodynamic calculations theory, Equilibrium wake model corrects the simplified model of aerodynamic calculations for the rotor.
平衡尾流模型基于风轮的稳态气动计算理论，考虑桨叶的尾流影响，对简化的风轮气动计算模型进行修正。
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