弯度翼型大迎角时分离涡流场的多平衡态现象  

Multi-equilibrium states phenomenon of separated flow for cambered airfoils at high incidences

作　　者：周乃桢[1] 叶正寅[1] 

机构地区：[1]西北工业大学,西安710072

出　　处：《应用力学学报》2012年第1期60-64,118,共5页Chinese Journal of Applied Mechanics

基　　金：国家自然科学基金(10872171)

摘　　要：基于kω的SST两方程湍流模型,在时间域求解雷诺平均Navier-Stokes方程,模拟弯度翼型大迎角时的分离流动。通过给翼型施加一定形式的扰动,重点关注了翼型弯度对大迎角分离涡流场平衡态转移的影响。研究结果表明:与相同厚度20%以上的对称翼型相比,2%弯度的翼型出现分离涡流场平衡态转移的起始迎角变小2°左右,迎角区间变宽约1°;在厚度相对较小的NACA2416翼型上也发现上述分离涡平衡态转移现象。由此说明翼型弯度在一定程度上促使了分离涡平衡态的转移。Coupled with SST turbulent model,the unsteady Reynolds-averaged Navier-Stokes equations are solved in the time-domain to obtain the steady and/or unsteady separated flows for cambered airfoils at high incidences.Certain kinds of vibrations are designed for the airfoils.The effects of the airfoil camber on multi-equilibrium states phenomenon for the separated flow are studied.It is found that multi-equilibrium states exist for the separated flows around the airfoils with camber of 2%.Compared with symmetrical airfoil of the same thickness which is larger than 20%,the range of incidences increase about 2° and start incidence decrease around 1°.The equilibrium state transition phenomenon occurs around the NACA 2416 airfoil with relatively small thickness.It is obvious that the camber of airfoil conduces to the equilibrium state transition phenomenon of separated flow to some degree.

关 键 词：弯度翼型 分离流 平衡态转移 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]