涡襟翼振动对三角翼涡的影响  

THE INFLUENCES OF FORCED OSCILLATIONS TOWARD VORTEX-BREAKDOWN

作　　者：陈言秋[1] 吕志咏[1] 李椿萱[1] 

机构地区：[1]北京航空航天大学

出　　处：《航空学报》1990年第9期A505-A509,共5页Acta Aeronautica et Astronautica Sinica

摘　　要：1.引言 许多实验表明,用主动干扰的方式是控制分离的一个有效方法,而且可以把分离区从一死水区(或紊乱的区域)变成一个有序流动区域。二维流动实验还表明非定常机动可以较大地改变流动结构。三维流态显示表明强迫振动对集中涡的形成过程等有显著影响,并影响涡和物面之间的距离。目前对三维非定常流动特性,以及非定常干扰对机翼绕流中涡破裂等的作用尚未充分了解。 影响集中涡破裂的关键因素是沿涡轴方向的压力梯度。涡环量对破裂的影响是双向的,涡强过大易使涡破裂;涡强过小时涡结构松散,也易于破裂,甚至迅速耗散掉。从二维结果看,非定常强迫扰动可使涡的结构更紧凑、清晰。The experimental results on the influences of oscillating leading edge vortex-flaps of triangular wing toward the vortex breakdown are presented in this paper. The results reveal that forced oscillations can delay the breakdown of concentrated vortices, and large reversed-flow regions which originally appears at the upper surface of the fixed wing at high angles of attack would be suppressed to some extent, depending on the oscillation frequencies. As a consequence, the influences can be optimized by selecting proper oscillation frequencies.

关 键 词：三角翼 涡流襟翼 振动 非定常流 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]