等速上仰翼型动态失速现象研究  

INVESTIGATION OF THE DYNAMIC STALL ABOUT THE PITCHING AIRFOIL^1

作　　者：白鹏[1] 崔尔杰[1] 周伟江[1] 李锋[1] 

机构地区：[1]北京空气动力研究所,北京100074

出　　处：《力学学报》2004年第5期569-576,共8页Chinese Journal of Theoretical and Applied Mechanics

基　　金：国家自然科学基金资助项目(10232010;10032060).~~

摘　　要：翼型大迎角绕流的静态失速将造成升力突降和气动性能急剧恶化,但利用非定常运动所产生的动态失速效应,可以大大地延缓气流分离和失速现象的发生.采用Rogers发展的双时间步Roe格式,求解拟压缩性修正不可压N-S方程.数值模拟了低雷诺数(Re=4.8×104)条件下NACA0015翼型作等速上仰(α=0°-60°)的动态失速过程,同Walker的试验结果比较,验证了计算结果的正确性.研究了该过程中主涡、二次涡和三次涡的发展,升力系数随攻角变化,以及不同上仰速度对动态失速效应所造成的影响.The static stall about the airfoil at the high angle of attack deteriorate the characteristics of aerodynamics rapidly. But this phenomena can be delayed effectively by the dynamic stall caused by the unsteady motion. The dual-step Roe schema developed by Rogers was used to solve the incompressible Navier-Stokes equations. Computationally simulated the dynamic stall about the pitching NACA0015 airfoil with identical pitching rate (α= 0°60°, at Low Reynolds number (Re = 4.8 x 104). And compared with Walker's experimental results to correct the CFD results. The developments of the main vortex, the second vortex and the third vortex, and the lift coefficient alteration to the angle of attack during the process were studied. Finally, the effects of the different pitching rate to the dynamic stall were compared.

关 键 词：失速 翼型 大迎角绕流 非定常运动 低雷诺数 气动性能 升力 延缓 动态 恶化 

分 类 号：O357[理学—流体力学] V211[理学—力学]