中-大迎角下圆锥前体流场的等离子体控制  

Plasma flow control over conical fore-body at moderate-high angles of attack

作　　者：赵帅[1] 李华星[1] 王健磊[1] 刘锋[2] 罗时钧[2] 

机构地区：[1]西北工业大学翼型叶栅国家重点实验室,西安710072 [2]美国加州大学尔湾分校机械与宇航工程系,尔湾926973975

出　　处：《实验流体力学》2012年第5期22-26,共5页Journal of Experiments in Fluid Mechanics

基　　金：西北工业大学基础研究基金(JC200901);国防科技重点实验室基金(9140C4201020901);高等学校博士学科点专项科研基金(200806990003;20106102110002);国家自然科学基金(11172243)

摘　　要：在圆锥-圆柱组合体圆锥段的尖端区域布置一对单个介质阻挡放电激励器(SDBD),通过风洞实验对圆锥前体分离涡流场的等离子体控制特性进行了研究。实验风速5m/s,迎角为25°和30°,采用表面压力测量技术,并通过对压力的积分得到侧向力系数。实验结果表明:通过控制激励器的开、关可以改变圆锥两侧压力分布不对称的模式,从而使得侧向力的大小和方向发生改变。研究表明:等离子体激励器可以对非双稳态下的圆锥前体分离涡流场进行有效的控制。A pair of single-dielectric barrier discharge （SDBD） plasma actuator was placed near the nose of the cone cylinder, and wind tunnel tests were performed to study the control effect of plasma actuators. The tests were carried out under the wind speed of 5m/s and at the an- gles of attack of 25° and 30° . The results consist of measurements of circumferential static pres- sure distributions. The overall side forces over the cone are calculated from the measured pres- sures. The test results show that the side force over the cone-cylinder model can be manipulated by activating the plasma actuators. The study indicates that even if the separation vortices flow filed is not bi-stable, the plasma active flow control is still effective.

关 键 词：等离子体 主动流动控制 细长圆锥体 非对称分离涡 单介质阻挡放电(SDBD) 大迎角 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]