带涡襟翼翼型流场的数值模拟  

Numerical simulation of the flow-field of an airfoil with eddy-flap

作　　者：白亚磊[1] 明晓[1] 丁涛[1] 

机构地区：[1]南京航空航天大学航空宇航学院,南京210016

出　　处：《计算力学学报》2010年第4期613-617,共5页Chinese Journal of Computational Mechanics

基　　金：国家973(2007CB714600)资助项目

摘　　要：以数值计算为手段,分析了带涡襟翼的翼型的流场特性,分别对迎角及扰流板偏角对翼型气动性能的影响做了分析。结果表明,在小迎角来流情况下,保持迎角不变,涡襟翼偏转角度越大,升力越小,阻力越大,呈现较好的线性关系。在大迎角情况下,绕翼型的流动发生分离,通过适当控制涡襟翼的偏转角度,能够有效的改善翼型的失速特性,从而达到流动控制的目的,迎角越大,涡襟翼所需偏转的角度越大。In this paper,the flow fields of an airfoil with eddy-flap are described by numerical simulation.The effect of attack angles and the eddy-flap angles on aerodynamic coefficient are studied.The results show that,at low angle of attack,the lift coefficient dropped and drag coefficient raised as the eddy-flap angle increased,.Their relationships are nearly lineal;while at the high angle of attack,the flow separated on the upper surface of the airfoil.The angle of attack increased,the angle of eddy-flap adjusting higher.The stall can be avoided by adjusts the eddy-flap angle properly as the result of flow control.

关 键 词：涡襟翼 分离流 流动控制 失速 

分 类 号：O35[理学—流体力学] TB937[理学—力学]