The desingularization smoothing parameter is introduced in calculating the induced velocity on trailing vortex surface.
在诱导速度计算中引入了非奇异光滑参数。
A modified trailing vortex wake model of propeller is introduced to describe the distortion and separation of the trailing vortex sheet.
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。
The coordinates of grids on the wing surface and dipole strength on the trailing vortex surface were changed with respect to time-stepping.
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 surface of propeller and its trailing vortex is divided into a number of small hyperboloidal quadrilateral panels with constant source sink and doublet distributions.
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 ejection from the half slot only blows away the vortex on the slot surface, and has little effect on the flow field near the trailing edge.
半开缝时，喷气的引入仅吹除了附着在开缝处的漩涡，对于尾缘处流场影响不大。
Due to the influence of radial positive pressure gradient, low-energy gas moves along trailing area to hub. That causes rapid dissipation and weakening of downstream passage vortex.
在叶栅下游，由于径向正压梯度的影响，低能气体沿尾流区向轮毂输运，引起下通道涡的迅速消散与衰减。
Airfoil trailing-edge vortex separation occurs, resulting in movement of the flow field near the airfoil stall.
翼型后缘出现的分离涡，导致翼型附近流场的流动失速。
In addition, the trailing edge jets may weaken or even eliminate the mixing phenomenon of the leading edge vortex, which is in advantage of the flight control of aircraft.
另外，后缘喷流可以减弱乃至消除前缘涡混掺现象的发生，进而有利于飞行器的操纵。
Once the trailing edge vortex stays at the trailing edge the interaction of complex vortex structures occurs and no longer has a beneficial effect on the suction peak induced by the stall vortex.
后缘涡在翼面上驻留时，各涡产生复杂的相互干扰，对失速涡在上翼面产生吸力有不利影响。
It is shown that in the present numerical investigations, the trailing edge shape and the reduced frequency have an important influence on the vortex evolution.
数值研究表明，后缘形状、折合频率等对涡结构演化有重要影响。
The system becomes overdetermined as zero vortex strength is set at trailing edge, to make the Kutta condition be satisfied.
为满足库塔条件而令后缘处涡强度为零，但导致了方程组的矛盾性。
A high suction peak is induced by the stall vortex as the trailing edge vortex sheds downstream smoothly.
后缘涡顺利地从后缘脱落时，失速涡在上翼面能诱导出较大的吸力。
A high suction peak is induced by the stall vortex as the trailing edge vortex sheds downstream smoothly.
后缘涡顺利地从后缘脱落时，失速涡在上翼面能诱导出较大的吸力。
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