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。
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。
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。
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。
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。
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。
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。
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。
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