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。
The method is only suitable for the nonlinear problem caused by detached vortex of wing before vortex breakdown.
该方法适用于翼面产生脱体涡流型或脱体涡占优(涡破裂前)所引起的非线性问题。
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。
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