rotor wake的例句大全

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.

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 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 measurements of hovering blade tip vortex and rotor wake were conducted to investigate the blade tip vortex formation and evolution, and its relationship with the rotor test states.

为了详细研究悬停旋翼桨尖涡的形成与发展过程，以及旋翼状态参数与桨尖涡及其尾迹的关系，开展了桨尖涡及其尾迹的测量和研究。

The unsteady Loading noise generated by interaction of a front rotor wake with an aft rotor in a counter-rotating ( CR) propeller is analyzed and the noise radiation formulae are derived.

本文着重研究了反旋桨扇前排转子尾流与后排转子干涉形成的非定常负荷噪声，并与试验结果作了对比。

Without any wake model, the pressure distributions are presented for two bladed rotor, the theoretical results show good agreement with experiment data.

在没有建立尾迹模型的前提下，计算了两叶旋翼在亚、跨声速时的压强分布，并将计算结果与国外实验数据作了对比，二者吻合程度良好。

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。

A calculation method of determining blade section drag in a rotor based on wake measurements

由尾迹测量确定转子叶型阻力的计算方法

The ATB tilt-rotor and the 5/ 6-scaled V-22 tilt-rotor were used as numerical examples and the free wake and induced velocity were calculated for hover flight. In order to validate the present method, the comparisons between calculations and available experimental data have been performed.

分别以ATB旋翼和缩比的V22旋翼为算例，计算了悬停状态的旋翼自由尾迹和诱导速度，并与可得到的试验数据进行了对比，验证了该方法的有效性。

Numerical Simulation on Interaction of the Free Wake of Helicopter Main and Tail Rotor

直升机主、尾桨自由尾迹相互干扰的数值模拟

CFD Simulation and Validation of Ducted Tail Rotor Numerical Simulation and Validation of Wake Field of Submarine with Stern Appendage

涵道尾桨的CFD模拟与验证带附体潜艇尾流场的数值模拟与验证

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 wake model and the second-order lifting line theory, a new analytical method is emphatically developed to predict the aerodynamic behavior of the advanced rotor with a swept, tapered or swept-tapered tip shape.

将该方法和桨叶二阶升力线模型结合，建立了一个新的适用于后掠、尖削及其组合形状的旋翼气动特性计算的分析模型。

a new combined wake/ cfd methodology is used to include realistic wake effects in cfd solutions for the rotor flow in hover.

一种新的组合自由尾流/CFD方法用于悬停旋翼流动的CFD解中以考虑实际尾流的作用。

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。

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。

An analytical method for predicting rotor vortex wake in low speed and hovering flight is described to investigate the motion of the helical tip vortex.

以重点考察旋翼尖涡的运动为目标来构想一种悬停和前飞旋翼涡尾流的理论计算方法。