应用等离子体进行翼型前缘分离控制的数值模拟研究  

Numerical research on airfoil leading edge separation control using plasma actuator

作　　者：薛帮猛[1] 杨永[1] 

机构地区：[1]西北工业大学翼型叶栅空气动力学国防科技重点实验室,陕西西安710072

出　　处：《空气动力学学报》2009年第1期1-4,共4页Acta Aerodynamica Sinica

基　　金：国防重点实验室基金(9140C4202020604)

摘　　要：将等离子体对中性气体的作用模型化为彻体力矢量,求解带源项的Navier-Stokes方程,数值模拟了等离子体激励器在NACA0015翼型大迎角下的分离控制效果,彻体力为净电荷在外加电场作用下的电场力。解拉普拉斯方程得到外加电场分布,等离子体中的净电荷分布由泊松方程给出。为了较好地模拟分离涡的发展,采用了雷诺平均与大涡模拟相结合的脱体涡模拟(Detached Eddy Simulation)方法。通过与实验结果对比,发现该模型能较好地模拟等离子体激励器的控制作用。Dielectric barrier discharge（DBD）, plasma actuator is modeled as body force vector resulting from external electric field and the net charge distribution in plasma. Navier-Stokes equations with body force source term are solved numerically to research leading edge separation control on NACA0015 airfoil. External electric field is calculated by solving Laplace equation and the net charge distribution from Poisson equation. To simulating separation flow well when plasma actuator off, Detached Eddy Simulation method is used. Comparision between simulation and experimental results shows that the model can give good prediction of plasma actuator effects for flow control.

关 键 词：等离子体 分离控制 脱体涡模拟 

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]