流动显示结果表明 ,喷流能有效地推迟双三角翼前缘涡的破裂 ,且随着攻角的增大 ,前缘涡破裂位置逐渐推后 ,喷流极大地改善了大攻角情况下前缘涡的非对称破裂特性 ,能有效地克服可能出现的机翼的“摇滚”现象 .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 . The flow shows that the jet flow can effectively delay the rupture of the leading edge vortex of the double delta wing. With the increase of the angle of attack, the vortex rupture position of the leading edge gradually pushes back and the jet flow greatly improves the situation of large angle of attack The asymmetric rupture of edge eddy can effectively overcome the possible “rock” phenomenon of the wing.In addition, the trailing edge jet can reduce or even eliminate the occurrence of front vortex mixing, which is beneficial to aircraft maneuvering.