摘要
对等离子体激励器做简化模型,并研究简化模型对于NACA0015翼型流动分离的控制效果。通过改变激励器在翼型上表面的位置及激励强度的大小,研究了实施流动控制的较佳位置及强度的大小。数值模拟结果表明,在前缘点附近加入控制的作用要优于其它位置;且激励强度对于流动控制的效果有极大的影响,大的激励强度有好的控制效果。此控制方法可以有效地延迟流动的分离,达到增升减阻的目的。是一种有前途的流动主动控制方法。
A simplified model for the plasma actuator is presented. The control effect of the plasma actuator on the flow over a NACA0015 airfoil is studied. Activation of the plasma actuator is found to delay flow separation and therefore stall of the airfoil at high angles of attack. The effectiveness of the actuator is found to be strongly dependent on the placement and intensity of the actuator on the airfoil. The most effective location is near the leading edge of the airfoil and the control effect depends
出处
《航空计算技术》
2007年第2期30-34,共5页
Aeronautical Computing Technique
关键词
流动控制
等离子体激励器
流动分离
flow control
strongly on the plasma intensity. plasma actuator
flow separation
