低雷诺数反齐默曼机翼的气动特性  

Simulation of an Inverse Zimmerman Wing at Low Reynolds Numbers

作　　者：李建华[1] 李锋[1] 

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《计算物理》2007年第1期49-53,共5页Chinese Journal of Computational Physics

摘　　要：通过PISO方法求解非定常不可压N-S方程,研究小展弦比反齐默曼机翼在低雷诺数下的流场特征,并分析其对气动特性的影响.结果显示前缘分离涡在反齐默曼机翼上表面形成一对集中涡.分析表明这对集中涡是影响反齐默曼机翼气动特性的主要因素,给机翼提供了较大的非线性升力和较大的失速攻角,前缘涡之间的相互影响使得机翼出现非定常现象和大攻角的非对称现象.与矩形翼相比,反齐默曼机翼有较好的稳定性.Unsteady incompressible Navier-Stokes equations are solved with a pressure correction method. A series of numerical calculations are conducted for Low-Reynolds-Number aerodynamics of an inverse Zimmerman wing. It shows that a pair of strong leading-edge vortex exist beyond the wing. They have strong effect on the inverse Zimmerman wing aerodynamics and offer high nonlinear lift and large stall attack angle. Interaction between the leading-edge vortexes results in unsteady and asymmetry phenomenon of the wing. The inverse Zimmerman wing shows a better longitudinal stability and flow-field stability.

关 键 词：微型飞行器 反齐默曼机翼 低雷诺数流动 前缘涡 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]