等离子体驱动器
物理
马赫数
机械
冲击波
边界层
休克(循环)
流量控制(数据)
粒子图像测速
阻力
流动分离
下洗
等离子体
边界层控制
光学
空气动力学
航空航天工程
介质阻挡放电
工程类
计算机网络
计算机科学
湍流
医学
量子力学
内科学
作者
Mengxiao Tang,Yun Wu,Haohua Zong,Shanguang Guo,Hua Liang,Yanhao Luo
出处
期刊:Physics of Fluids
[American Institute of Physics]
日期:2021-06-01
卷期号:33 (6)
被引量:29
摘要
Particle image velocimetry measurement on shock wave/boundary layer interaction in a Mach 2.0 supersonic wind tunnel is performed to quantitatively reveal the plasma flow control effect in this paper. The typical flow structure is produced by a 24-degree compression ramp model and the streamwise plasma actuator array with five pulsed spark discharge plasma actuators is adopted as the control device. In the midspan plane, the results show that although the separation region exhibits an obvious extension, the foot of the separation wave moves upstream and the shock wave angle decreases from 41.6° to 22.3°, proving the decline in shock intensity. The shock wave drag is estimated to be reduced by 45%. According to the phase-averaged velocity field, the reason that the high-frequency actuation plays a key role in achieving the continuous control effect is revealed through the temporal evolution of the separation region area. Also, another interesting phenomenon that the flow deflects when passing through the actuation region is found, which may induce the upwash and downwash motions of the boundary layer and further reduce the flow separation on both sides of the actuation region. At last, a preliminary conceptual model is proposed to reveal the probable flow control mechanism.
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