基于被动标量格子Boltzmann方法的翼型绕流数值模拟  

Numerial Simulation of Flow around Airfoil Using Passive Scalar Lattice Boltzmann Method

作　　者：郑佩[1] 

机构地区：[1]西北工业大学航空学院,西安710072

出　　处：《科学技术与工程》2011年第13期2990-2993,2998,共5页Science Technology and Engineering

摘　　要：采用格子Boltzm ann方法(lattice Boltzm ann m ethod,LBM)中的被动标量模型,不考虑温度的影响,采用合适的密度分布函数和碰撞处理,并在一般坐标系下完成迁移过程的插值。固壁边界条件采用无滑移边界条件,模拟了雷诺数为60 000,攻角分别为0度和8度状态下的NACA0012翼型绕流。其翼型表面流线图和压力云图分布结果均与D2Q9模型结果吻合较好,证明该方法能够很好的模拟低速翼型的绕流。并且,在方程中加入等离子体激励器简化的作用力模型,初步达到带攻角下流动分离的控制效果,证明了该方法在带有体积力项流动的数值模拟方面的优良特性。Using the passive scalar lattice Boltzmann method without the effect of temperature,the flow around NACA0012 at zero and eight angel of attack at 60 000 Reynolds number is simulated.The proper particle equilibrium distribution function and collision operation are choosed,by using generalized form of interpolation supplemented method for particle streaming.Then non-slip boundary condition for the solid wall is applied.The pressure distribution and streamline agree well with the results of the D2Q9 model.Then source term of the force on the leading edge of the airfoil are added.The result proves that the flow separation around the airfoil has been controlled at angle of attack of eight degrees and the good characters of this method.

关 键 词：格子BOLTZMANN 被动标量法 翼型绕流 流动控制 

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]