合成射流对角区马蹄涡的影响研究

Effect of Synthetic Jet on Horseshoe Vortices in Junction Region

为削弱角区马蹄涡的强度,采用数值模拟的方法研究合成射流对角区马蹄涡的影响。在翼-平板交接处的平板上加载生成合成射流的控制腔,利用动网格技术模拟合成射流,使得控制腔底部壁面周期性振动。分析了合成射流对流场涡量、端壁表面摩擦系数和端壁表面压力的影响。结果表明,合理选择合成射流可以有效抑制机翼根部流场的三维分离,在分离点前X/T=-0.6位置引入合成射流可以使马蹄涡腿更向机翼壁面靠拢,在分离点后X/T=-0.33位置引入合成射流几乎可以完全消除马蹄涡。合成射流可以有效减弱马蹄涡在壁面的摩擦阻力。最后对合成射流的控制机理进行了讨论。

In order to reduce the strength of horseshoe vortex, numerical simulation method was adopted to study the effects of synthetic jet on horseshoe vortices. Control cavity was installed upstream of the junction. Synthetic jet was performed by using dynamic mesh technique and bottom of control cavity was moved by periodic vibration mode. The effects of synthetic jet on vorticity, skin friction coefficient on the flat plate, pressure field of flat plate surface and periodic variation of control state caused by synthetic jet were analyzed in this paper. The results demonstrate that reasonable choice of synthetic jet can effectively suppress the three-dimensional separation at the junction flow field. Horseshoe vortex legs move closer to the wing when synthetic jet is installed at the location of X/T=-0.6, which is up- stream of the separation point. Horseshoe vortices almost disappear when synthetic jet is installed at the location of X/ T=-0.33, which is downstream of the separation point. The skin friction on the plate is reduced due to the synthetic jet. The control mechanism was discussed at last.