转捩对S809翼型气动特性影响的数值模拟  

NUMERICAL SIMULATION OF TRANSITION EFFECT ON AERODYNAMIC PERFORMANCE OF AEROFOIL S809

作　　者：钟伟[1] 王同光[1] 王强[1] 

机构地区：[1]南京航空航天大学空气动力学系,南京210016

出　　处：《太阳能学报》2011年第10期1523-1527,共5页Acta Energiae Solaris Sinica

基　　金：国家重点基础研究发展(973)计划(2007CB714600);江苏省创新学者攀登项目(BK2008044);江苏省普通高校研究生科研创新计划(CX09B_069Z)

摘　　要：以S809翼型为例分析了转捩对水平轴风力机翼型气动特性的影响。首先采用多种湍流模型对S809翼型开展了全湍流数值模拟,观察了忽略转捩条件下的翼型升阻力特性,然后开展了考虑转捩的数值模拟,分析了转捩对翼型升阻力特性和尾缘分离的影响。结果表明,在附着流动状态下,数值模拟中忽略转捩会导致翼型升力系数被低估约10%,阻力系数则被成倍高估;转捩对翼型尾缘分离也有一定影响,转捩点越靠近前缘,尾缘附近附面层速度型的饱满程度降低,抵抗逆压梯度的能力减弱,尾缘分离越容易发生。An analysis of laminar/turbulence transition effect on the aerodynamic performance of aerofoil S809 was made. Firstly, a full turbulence simulation was carried out with multiple turbulence models to observe the lift and drag characteristics ignoring transition. Then a simulation with transition prediction was performed, and the effect of transition on the lift and drag characteristics as well as the flow separation near the trailing edge was investigated. It is shown that the lift coefficient can be underestimated by about 10% and the drag coefficient can be doubled, if the transition is ignored in the simulation. The flow separation near the trailing edge is also affected by transition. As the transition point moves towards the leading edge, the velocity profile of the boundary-layer near the trailing edge becomes less full so that the ability to resist adverse pressure is weakened and the flow separation near the trailing edge more likely happens.

关 键 词：风力机 S809翼型 转捩 CFD数值模拟 

分 类 号：TM614[电气工程—电力系统及自动化]