为获得带有襟翼的机翼尾涡的合并动力学过程,在验证数值方法的基础上,数值模拟带有襟翼的机翼绕流尾流场,根据涡合并特征将合并过程划分为诱导共转阶段、合并阶段和轴对称化阶段.采用涡间距量纲—化尾流区域描述二涡诱导合并.变换弦长雷诺数、襟翼翼梢与机翼翼梢的间距、襟翼角度,改变襟翼翼梢涡与机翼翼梢涡的强度比,得到尾涡合并差异的特征.计算结果表明:随着雷诺数的增加涡的强度增加,涡量的扩散程度减低,涡合并过程被推迟,空间诱导运动过程得到延长,涡系空间诱导运动增强,涡合并的雷诺数效应随着雷诺数增加而减弱,缩短涡间距,加速涡合并过程,但合并后的远场涡尺寸和形态没有显著改变;襟翼涡随着襟翼角的减小而减弱,强度逐渐减弱的襟翼涡逐步被翼梢涡拉伸卷吸,微弱的襟翼涡系在近场中的合并过程完全改变,翼梢涡的运动轨迹并未受到诱导运动.翼梢涡合并的雷诺数效应表现为诱导运动过程的增强,尾流中强度小的涡系起不到明显的诱导作用. In order to obtain the combined dynamics of wing-tail vortices with flaps, numerical simulation is performed on the numerical method to simulate the wing wake wake field with flaps. The merging process is divided into induction Co-transfer stage, the merger stage and the axisymmetric stage.Using vortex spacing dimension - the wake area to describe the second-vortex inductive merging.Changing the chord Reynolds number, the distance between the flap wing tip and the wing tip, the flap angle, The results show that as the Reynolds number increases, the vortex intensity increases, the degree of vorticity diffusion decreases, the vortex merging process is delayed and the space is induced Reynolds number effect of eddy coalescence decreases with the increase of Reynolds number, shortening the vortex spacing and accelerating the process of vortex integration, but the size and shape of the far-field vortex merged have no significant changes; The wing vortices weaken as the flaps angle decreases, and the gradually weakening flaps vortexes are gradually entangled by the wing tip vortex. The merging process of the weak flap vortex lines in the near field is completely changed. The wing tip vortex Motion track and Motion is induced. The combined tip vortex Reynolds number effects such as inducing enhanced movement of small intensity wake vortices not achieve significant induction effect.