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1·An analysis of periodic flow streamlines shows that it is probably due to the effect of leading edge vortex.

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。

2·The effects of coupled motion on the leading edge vortex and aerodynamic character of the wing were analyzed.

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。

3·The leading edge vortex breakdown can be delayed using supplements to change the flow field over upper surface of the wing.

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。

4·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.

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。

5·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.

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。

6·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。

7·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.

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。

8·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.

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。

9·Velocity gradient, pressure gradient and circulation gradient are used to model the separated vortex flow field over a leading edge delta wing.

用速度梯度、压力梯度和环量梯度模拟大攻角尖前缘三角翼流场。

10·The shedding cycle of jet hole vortex in leading edge is shorter than that of downstream.

前缘射流孔旋涡的脱落周期比下游射流孔旋涡脱落周期短。