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.
出处
《空气动力学学报》
EI
CSCD
北大核心
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)
关键词
等离子体
分离控制
脱体涡模拟
plasma
separation control
detached-eddy simulation
