【作者】 黄烁桥； 申功炘； Robert Konrath； Carl F.v.Carmer； Kompenhans Jürgen；

【Author】 Huang shuoqiao~1,Shen Gongxin~1 Robert Konrath~2,Carl F.v.camer~2,Kompenhans Jrgen~2 1 Institute of Fluid dynamics,School of Aeronautic Science and Technology,Beijing University of Aeronautics and Astronautics,Beijing 100083,China 2 Institute of Aerodynamics and Flow Technology,Germany Aerospace Center(DLR),Gottingen,Germany

【机构】 航空工程与科学学院流体所北京航空航天大学； Institute of Aerodynamics and Flow Technology,Germany Aerospace Center(DLR),Gottingen,Germany；

【摘要】 利用简化的飞机模型,通过改变尾翼的迎角及展弦比,试图建立一种能加速自我消亡的尾流涡系统。本实验在拖曳水槽中进行,运用SPIV系统进行测量,获得了一系列空间切面的2D/3C数据,给出两种不同尾翼情况下的SPIV观测结果,并与无尾翼情况作了对比:若没有尾翼,翼尖涡能单独地存在很长时间,而如果选用合适的尾翼设置,由于尾翼涡和翼尖涡相互作用触发出的Rayleigh-Ludwieg不稳定性(The Rayleigh-Ludwieg instability),尾迹涡的涡核可以在飞机下游约35个展长位置处就破裂掉;另外,为了有效地使尾迹涡破裂,必须使Rayleigh-Ludwieg不稳定性的"触发"发生在翼尖涡完全发展后,触发时间的控制可通过调整尾翼迎角及展弦比来实现。更多还原

【Abstract】 An experimental study with a simplified model was carried out to establish a self-destructing vortex wake by changing the attack angle and wing aspect ratio of the horizontal tail wing(HTW).A SPIV system was employed in a water towing tank to obtain sets of 2D/3C data in different special slices.The results from two kinds of tail settings are exhibited and compared with one case without HTW.The conclusion is by using suitable HTW settings the wake vortex cores could be destabilized as early as 35 wing spans in downstream location because of the Rayleigh-Ludwieg instability triggered by the interaction between the tail vortex and wing-tip vortex, instead of a very long time for one with tail;and this"trigger"should be occurred after the wing-tip vortex develops completely to make sure the vortex cores’ destruction,the timing can be controlled by adjusting the attack angle and wing aspect ratio of the HTW.更多还原