用该方法研究了近地升力面尾涡卷起的地面效应。
The improved vortex lattice method is used to predict the ground effect on wake roll-up behind a lifting surface.
翼表面网格坐标和尾涡面上的偶极强度随时间步进变化。
The coordinates of grids on the wing surface and dipole strength on the trailing vortex surface were changed with respect to time-stepping.
本文在考虑了尾涡收缩的同时，还计入了桨叶梢涡分离。
Not only the wake contraction but also the tip vortices separation has been taken into account.
结果表明：粘性耗散与塔架效应是引起尾涡变形的主要原因。
The result shows that viscidity dissipation and tower effect are main reasons of wake eddy distortion.
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 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.
计算了圆柱的升阻力系数、尾涡脱落频率等描述绕流问题的主要参量。
Such parameters of flow characteristics are investigated as lift and drag coefficient and vortex shedding frequencies.
在小进距比的重载情况，螺旋桨尾涡的收缩对螺旋桨的性能影响较大。
In the case of heavy load when the advance ratio of propeller is small, the contraction of wake has large effect on the performance of the propeller.
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。
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.
采用圆柱刚性尾涡模型，并作高效近似处理，几个算例表明，计算值与实验值相符合。
Cylinder rigid wake model has been adopted and the approximate treat in high efficiency. The results carried out for examples shows good agreement with experiments value.
采用了一个修正的螺旋桨尾涡模型，来模拟导管螺旋桨尾涡片的扭曲变形及分离现象。
A modified trailing vortex wake model of propeller is introduced to describe the distortion and separation of the trailing vortex sheet.
比较了几种气液传质模型，讨论了气泡大小分布和气泡尾涡加速效应对气液传质的影响。
Several classical models for the gas-liquid mass transfer coefficient were compared, and the influences of the bubble size distribution and bubble wake effect were discussed.
采用大涡模拟方法可以分析和计算近地阶段尾涡消散和运动规律，但模型繁琐、计算复杂。
The large eddy simulation methods can be used to analysis and calculate the decay and transport rules of wake vortex in near ground phases, but it′s too complex and difficult to use.
螺旋桨表面和它的尾涡面离散为四边形双曲面元，每个面元上布置等强度偶极子和源汇分布。
The surface of propeller and its trailing vortex is divided into a number of small hyperboloidal quadrilateral panels with constant source sink and doublet distributions.
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。
The effect of helicopter fuselage on its rotor is studied using a simplified free-wake model.
这个系数考虑到了在固体颗粒上吸附的气体，尾涡和乳化相之间的交换以及在这个体系中的滞留量。
This factor accounts for the gas adsorbed on the solids, its interchange between the wake and the emulsion, and its holdback in the system.
该文应用低阶速度势面元法建立了预报三维水翼水动力性能的数值方法，重点对翼梢和尾涡进行了研究。
A potential-based surface panel method is applied to predicting the performance for three-dimensional hydrofoils, with emphasis on the tip region.
计算了雷诺数为8.9 ~ 1000.0时圆球绕流受到的阻力，分析尾涡形状及长度随雷诺数的变化规律。
The drag on the sphere was calculated for Reynolds numbers8.9to1000.0, and the shape and length of the wake behind the sphere were investigated.
进一步优化螺旋桨尾涡模型，并进行了实例计算与试验结果、原计算结果对比分析，结果表明改进后的尾涡模型计算结果具有更高的精度。
Practical sample is calculated and experimental test is carried out. Comparison with the previous result shows that the improved wake model gives resalls with higher accuracy.
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。
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.
它们使用的操纵和控制系统大多是由多个螺旋桨推进器组成的，这样的系统体积大、重量大、能耗高、综合效率低，并有较大的噪音和尾涡。
Their maneuvering and control systems are made up of several propellers. This system has many disadvantages such as big volume, high consuming of energy, low total efficiency , high noise and vortex.
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。
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.
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 wake is mixing with the last rotor tip leakage vortex in the stator passage, leading to more substantial fluctuations in the flow field.
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 rotor tip leakage vortex has a stronger influence on the downstream endwall flow than the rotor wake.
动叶尾迹强度明显减弱，叶背流动分离得到抑制，叶尖泄漏涡也得到了周期性的抑制。
The intensity of rotor wakes was reduced, flow separation on rotor suction side was suppressed and the tip leakage flow was suppressed periodically.
本文采用LIF(激光诱导荧光)流动显示和PIV(粒子图像速度场仪)测量对横流冲击射流的尾迹涡结构进行了实验研究。
The wake vortices of an impinging jet in crossflow were studied experimentally by means of laser-induced fluorescence (LIF) flow visualization and particle image velocimetry (PIV) measurement.
结合探针信号的自相关函数，研究流场湍流结构，发现近尾可能存在大涡拟序结构，而在远尾则没有湍流。
By studying the autocorrelation function of the probe signal, it is found that the large eddy quasi ordering structure likely exists in near wake, but there is no turbulence in far wake.
结果表明，一次风射流由于与上游横向射流的相互作用，在背火侧形成尾迹涡，在向火侧形成剪切涡。
It is showed that being the interaction between primary air and upstream fluid, the shear eddy the the wake are formed on the two sides of the primary air respectively.
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。
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.
由实验结果可得到两种明显的尾迹涡结构、即射流尾迹涡和横流尾迹涡。
Two kinds of distinctive wake vortices were identified from the experimental results, namely the jet wake vortices and the crossflow wake vortices.
由实验结果可得到两种明显的尾迹涡结构、即射流尾迹涡和横流尾迹涡。
Two kinds of distinctive wake vortices were identified from the experimental results, namely the jet wake vortices and the crossflow wake vortices.
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