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本文中利用三角翼前缘涡襟翼的强制振动来推迟涡破裂。流场显示实验结果表明,在有强制扰动时,集中涡显示出两种不同形式的破裂,可分成六种不同的破裂形态。非定常集中涡的一个破裂过程涉及几种破裂形态之间的转换。涡襟翼振动产生的非定常效应对涡破裂的影响与三角翼后掠角有密切的关系,随后掠角增大非定常效应的影响变小。就实验迎角范围而言(α<35°),对50°后掠角三角翼,涡襟翼振动可显著推迟涡破裂;但对70°后掠角三角翼,振动却能促进涡的破裂。涡襟翼振动改变了集中涡的性态,使集中涡趋向于和前缘平行。振动对涡破裂的作用部分地与这种效应有关。
In this paper, the vortex rupture is delayed by the forced vibration of the delta wing leading edge vortex flap. The experimental results of the flow field show that the concentrated vortex shows two different types of ruptures and can be divided into six different ruptures when there is a forced disturbance. A rupture process of unsteady concentrated vortex involves the conversion between several rupture patterns. The effect of unsteady vortex flap flaps on the vortex rupture is closely related to the sweep angle of the delta wing, and then the effect of the unsteady sweep on the unsteady side becomes smaller. For the experimental range of attack angle (α <35 °), the vibration of vortex flaps can significantly delay the vortex rupture for the 50 ° sweep angle delta wing; however, for the 70 ° sweep angle delta wing, vibration can promote the vortex rupture . Vortex flap vibration changes the state of concentrated vortex, so that the concentrated vortex tends to be parallel with the leading edge. The effect of vibration on the vortex rupture is partly related to this effect.