前体不对称涡占空循环等离子体流动控制机理研究  

The Study of Flow Control Based on Duty-cycled Plasma Actuators for an Asymmetric Vortex Pair over the Slender Forebody

作　　者：李尹喆[1] 蔡晋生[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,西安710072

出　　处：《科学技术与工程》2011年第11期2537-2542,共6页Science Technology and Engineering

摘　　要：针对大迎角状态下,流动绕过顶角为20°的圆锥-圆柱组合体模型产生的一对不对称分离涡,通过等离子体激励器对其进行主动控制,并对控制过程机理进行了分析。实验在实验段为3.0 m×1.6 m的低湍流风洞中进行,实验攻角是45°。基于圆锥体底部直径的雷诺数为50 000。等离子激励器为一对,分别位于实验模型顶部左右两侧,通过频率为10 Hz的占空循环调节,交替对流动产生扰动。实验数据表明,当带有占空循环的激励作用时,分离涡的变化成周期性趋势,并在两个相似于双稳态分离涡型态之间过渡。实验结果表明,当左右激励器在一个占空循环周期中交替开启时间相等时,几乎消除了原有不对称分离涡产生的侧力,实现对不对称分离涡稳定性的控制。A mechanism study of active plasma actuations over a flow of an asymmetric vortex pair generated at the leeward of a 20°circular-cone-cylinder model at high angle of attack is presented.The tests are carried out at an angle of attack of 45°in a low-turbulence,low-speed wind tunnel of which the test section is 3.0 m×1.6 m.The Reynolds number based on the cone base diameter is 50 000.A pair of Single-Dielectric-Barrier-Discharge（SDBD） plasma actuators symmetrically located at starboard and port of the apex of the model respectively,alternately produce perturbations to the flow by duty-cycled control the frequency of which is 10 Hz.The experiment data demonstrate the separation vortex pair varies periodically and smoothly between two opposite states similar to the bi-stable patterns.The side force generated by the original asymmetric vortex pair is eliminated when the starboard and port actuators share the time equivalently in the duty-cycled period.

关 键 词：不对称分离涡 大迎角空气动力学 流动控制 等离子体 

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]