基于几何变形翼型的流动分离控制  

FLOW SEPARATION CONTROL ON MORPHING WING

作　　者：侯粉[1] 徐敏[1] 陈志敏[2] 

机构地区：[1]西北工业大学航天学院,西安710072 [2]西北工业大学航空学院,西安710072

出　　处：《工程力学》2009年第5期228-233,238,共7页Engineering Mechanics

基　　金：博士点基金国防基础预研项目(20070699054)

摘　　要：基于连续振动的几何变形法,应用弹簧近似的动网格技术,在雷诺数Re=5×104,迎角α=3°的条件下,对NACA4415翼型进行了流动控制的数值模拟,研究了振动位置、振动频率和振幅对分离流场特性影响的机理,分析了振动特性对翼型升力系数和阻力系数的影响效应。计算结果表明:1)振动位置越靠近分离点,越有助于减小分离;2)振动频率大于涡脱落的自然频率时,分离流场能达到明显地改善;3)在所研究情况下,振幅为0.00512倍弦长时,翼型获得最大平均升阻比。The unsteady flow around NACA 4415 airfoil is numerically simulated at Re=5×10^4, α=3°, and continuous deforming technique based on morphing wing is applied to control flow separation through spring analogy method. The effects of various oscillation parameters （position, frequency, and amplitude） on separated flow characteristics and the coefficients of lift and drag are analyzed respectively. The results show that： 1） the closer the oscillation position is to the separated point, the more significantly the flow separation is reduced; 2） the separated flow can be improved effectively when the oscillation frequency is higher than the natural frequency of vortex shedding from the upper surface; 3） The average lift-to-drag ratio is maximized when the amplitude is 0.00512 times of the chord of airfoil.

关 键 词：流动控制 变形翼型 弹簧近似法 低雷诺数 非定常分离流 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]