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。
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。
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。
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