摘要
设计了一种新型的大迎角主动流动控制方法。采用圆锥-圆柱组合体模拟飞行器前体,在靠近圆锥尖端处镶嵌了一对马蹄形单电极介质阻挡放电(Single-Dielectric Barrier Discharge SDBD)等离子体激励器,通过风洞实验研究了等离子体激励器在不同状态下对大迎角模型前体的非对称气动载荷的控制作用。实验结果表明,通过控制等离子体激励器的开闭可以使得圆锥-圆柱组合体在大迎角下出现的侧力改变方向。还对通过调节单侧等离子体激励器的激励电压实现圆锥前体侧力系数在正负极值间连续变化的可能性进行了初步的实验探索。
A new method of active flow control at high angle of attack is under developing. A pair of plasma actuators of horseshoe-shaped paced near the nose of the slender body is proposed for dynamic manipulation of forebody aerodynamic loads at high angles of attack. Surface pressure measurement was employed in wind tunnel test, and the pressure distribution on the model shows that asymmetric side force over the cone-cylinder model could be manipulated by activating the plasma actuators. A preliminary study was conducted to assess the control law of the side forces on the slender body at high angles of attack by adjustment of the excitation voltages of plasma actuators.
出处
《实验流体力学》
EI
CAS
CSCD
北大核心
2010年第2期34-38,共5页
Journal of Experiments in Fluid Mechanics
基金
西北工业大学基础研究基金(NPU-FFR-W018102)
高等学校博士学科点专项科研基金(200806990003
2009610220001)资助
