Computational Analysis of Unsteady Flow-fleld Induced by Plasma Actuator in Burst Mode
Computational Analysis of Unsteady Flow-fleld Induced by Plasma Actuator in Burst Mode
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DOI：
10.2514/6.2010-5090
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发表时间：
2010-06
期刊：
影响因子：
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通讯作者：
K. Asada;K. Fujii
中科院分区：
文献类型：
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作者：
K. Asada;K. Fujii
为了阐明等离子体激励器控制翼型前缘分离的突发模式效应这一重要现象，采用大涡模拟方法对NACA0015翼型等离子体激励器控制流场进行了数值模拟。在正常模态下，翼型前缘附近存在较大的气泡，而在破裂模态下，气泡比正常模态短。此外，通过对分离流控制过程的观察，阐明了等离子体激励器在爆发模式下产生的展向涡诱导了自由流方向的强涡，并将动量从自由流传递到边界层。
In order to clarify the important phenomenon for the burst mode effect of the plasma actuator on the control of leading edge separation over an airfoil, The flow-field controlled by plasma actuator over the NACA0015 airfoil is analyzed using Large Eddy Simulation. While the flow has the large bubble near the airfoil leading edge in normal mode, the bubble is shorter than normal mode in burst mode. In addition, observing the process of controlling the previously separated flow, it is clarified that the free stream directional strong vortices are induced by the span directional vortex generated by the plasma actuator in burst mode, and it transfers momentum from the free stream to the boundary layer.