翼型前缘分离流动在等离子体激励器控制下的响应  

Airfoil Leading Edge Separation Flows Under Control of 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：《计算物理》2008年第6期689-693,共5页Chinese Journal of Computational Physics

基　　金：国防重点实验室基金(9140C4202020604)资助项目

摘　　要：将等离子体对中性气体的作用模型化为彻体力矢量,采用DES(Detached Eddy Simulation)和DDES(Delayed-Detached Eddy Simulation)方法,求解带彻体力源项的Navier-Stokes方程,研究NACA0015翼型16°迎角下,前缘分离流动在等离子体激励器控制下的响应过程.激励器工作后,DDES计算结果显示,分离流动经历一个渐近的再附过程;DES计算因发生网格诱导分离,得到了非定常的响应过程.Plasma actuator is modeled as body force vectors resulting from external electric field and net charge distribution in plasma. Leading edge separation flows around NACA0015 airfoil under control of plasma actuator is simulated by Navier-Stokes equations with body force source which are solved by detached eddy simulation（DES） and delayed-detached eddy simulation （DDES）. With actuator on, the separation flow reattached through an asymptotic progress in DDES simulation. An unsteady response occurs in DES due to grid induced separation.

关 键 词：等离子体 分离控制 脱体涡模拟 延迟脱体涡模拟 

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]