二元翼型大迎角绕流的平衡态(解)的数值研究  

Numberical simulation of separation equilibrium of flow around 2D wing configuration at high angle of attack

作　　者：祝明红[1,2] 叶正寅[3] 金玲[1,2] 

机构地区：[1]中国空气动力研究与发展中心空气动力学国家重点实验室,四川绵阳621000 [2]中国空气动力研究与发展中心,四川绵阳621000 [3]西北工业大学航空学院,陕西西安710072

出　　处：《空气动力学学报》2012年第4期477-482,共6页Acta Aerodynamica Sinica

摘　　要：基于k-ω的SST两方程湍流模型,在时间域求解雷诺平均Navier-Stokes方程(RANS)计算了翼型大迎角分离流动。通过给翼型施加不同形式的扰动,重点关注了不同扰动形式对翼型大迎角分离涡流场平衡态的影响。研究表明:在所给定的百万雷诺数条件下,当翼型厚度达到一定程度而且在一定迎角范围内时,翼型的分离涡流场存在多个平衡态,且在一定扰动条件下会发生平衡态转移现象。在不同振动形式上,沉浮和俯仰比前后振动更易激发平衡态的转移。正是这种分离涡流场平衡态的多值现象,可能引发风洞实验中大迎角气动力数据的分散。The Reynolds-Averaged Navier-Stokes （RANS） method is conducted to simulate flow around airfoil at high AOA. The separation is well captured using two-equation shear stress transport （SST/k-w） turbulence model accounting for turbulence motions. Calculation shows that the wing separation vortices are stable in several equilibrium stats, with the wing thickness up to a certain criteria, and AOA in a certain range. Meanwhile the separation transfers from one stable state to anther when certain disturbance is intruded. Comparing different disturbances, the translation is inclined to happen under heaving-pitching motions rather than forward-afterward vibrations. That is the exact one of most important reasons for aerodynamic loads data variation of airfoil at high AOA in wind tunnel test.

关 键 词：分离流 稳定性 重复性 

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]