摘要
将纳秒脉冲驱动的介质阻挡放电等离子体激励器应用到NASA SC(2)-0712翼型上,在迎角分别为15°和20°时,开展了在不同雷诺数下的分离流动控制研究。通过模型表面静压测量,得到了不同激励频率下的分离流动控制效果。对翼型表面压力进行分布积分,得到了在不同雷诺数和激励频率下的升力系数,表明分离流的控制效果有一个较宽的激励频率范围,只要激励频率落在相应的频带范围内,均能实现有效的分离抑制。流动显示结果表明,分离流的控制在瞬时表现为放电后可形成大尺度旋涡拟序结构。旋涡的周期性产生、运动和演化造成了分离剪切流动的动态变化过程,从而促进了高/低速气流的动态掺混。
The nanosecond pulsed plasma discharge actuator is used on a NASA SC（2）-0712 airfoil. At the angles of attackof 15° and 20°, the flow control efficacy of the actuators is tested at a series of Reynolds number conditions. The static pres-sure test result shows that the actuator has different control effect at different forcing frequencies. By calculating the lift coef-ficient, the relations between the forcing frequency and lift are determined, which shows that the broadband bandwidth offlow reattachment makes the flow control more practicable. The flow visualization test shows that the pulse discharge promotes the formation of large scale vortexes. The coherent structures of the vortex couples are periodically produced, moveand evolution. This process brings the separated shear layer dynamic evolution, and thus promotes a dynamic mixing ofhigh/low speed airflow to happen in the separated flow region.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2016年第7期2102-2111,共10页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金(11532007)
中央高校基本科研业务费专项资金(NP2014605)
江苏省研究生培养创新工程(KYLX_0216)
南京航空航天大学基本科研业务费资助项目(NS2013013)
南京航空航天大学研究生创新基地(实验室)开放基金(kfjj201401)~~
关键词
纳秒脉冲
等离子体
分离流
流动控制
旋涡
拟序结构
nanosecond pulses
plasma
separated flow
flow control
vortex
coherent structures
