应用等离子体进行翼型升力控制的数值模拟研究  

Numerical Research on Airfoil Lift 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：《航空计算技术》2008年第1期9-11,共3页Aeronautical Computing Technique

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,数值模拟了在NLF(1)-0213翼型上表面60%弦长处安装等离子体激励器对升力的控制效果。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。升力线计算结果与实验值吻合,激励器工作时,升力线向上平移,控制效果与襟翼类似。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 lift control on NLF（ 1 ） -0213 airfoil with plasma actuator at 60% chord length. External electric field is calculated by solving Laplace equation and the net charge distribution from Poisson equation. Calculated lift curve agree with experimental results and lift curve is shift up when actuator on. The effect is similar to flap.

关 键 词：等离子体 升力控制 N—S方程 

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]