通过对沉浮运动一个周期流线图的分析，认为这是翼型前缘涡的影响造成的。
An analysis of periodic flow streamlines shows that it is probably due to the effect of leading edge vortex.
由于前缘涡的影响，翼型厚度增加，平均压差阻力系数变小，甚至会出现负值。
As airfoil thickness is increased, the average pressure drag, affected by leading edge vortex is reduced even to be negative, and meanwhile friction has little increase.
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。
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.
三种相位下的涡流场形态各有不同，上挥（下拍）初期前缘涡的运动主要存在两种形态。
The flow fields are different for the three phase motion patterns and there are two types of leading-edge vortex motion at an earlier stage of upstroke or downstroke.
本论文主要是通过实验来研究细长圆锥体在大迎角下的绕流流场的特性和细长三角翼加背鳍后对前缘涡的影响，检验相关理论结果。
This paper deals with the numerical solution of the Euler equation for airfoils using approximate boundary conditions and the effects dorsal fin on vortex over delta wing at high angles of attack.
利用附加的小辅助件，改变翼面上方的流场，使机翼前缘肌体涡推迟破裂。
The leading edge vortex breakdown can be delayed using supplements to change the flow field over upper surface of the wing.
分析了耦合运动对前缘分离涡和气动特性的影响，以及不同相位角和不同频率对耦合气动特性的影响。
The effects of coupled motion on the leading edge vortex and aerodynamic character of the wing were analyzed.
本文还分析了前缘分离涡破裂前后的流动现象和旋涡横截面流线图谱的变化规律。
This paper also presents analysis of the flow features ahead and behind of the leading edge vortex breakdown and the topological features of section streamlines.
采用差分方法计算旋涡流场，进而分析三角翼上前缘分离涡的运动特点及其破碎机理。
The vortex flow field is calculated with difference methods, and the motion characteristics and the bursting mechanism of the leading-edge separated vortices of delta wing are analyzed.
细长翼翼面上方的前缘集中涡是控制机翼绕流和影响机翼气动力特性的主要因素。
The leading edge vortices are important factor to control the flow field around the slender-wing and to influence the aerodynamic characteristics of the wing.
研究显示，前缘分离涡破裂后，流动的非定常脉动特性非常明显，这种非定常效应对机翼气动弹性特性的影响不可忽略。
It is shown that the unsteady fluctuation characteristics of the flow become highly obvious after the vortex breakdown, which exert a significant impact on the aeroelastic characteristics of the wing.
研究显示，前缘分离涡破裂后，流动的非定常脉动特性非常明显，这种非定常效应对机翼气动弹性特性的影响不可忽略。
It is shown that the unsteady fluctuation characteristics of the flow become highly obvious after the vortex breakdown, which exert a significant impact on the aeroelastic characteristics of the wing.
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