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

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.