纳秒脉冲等离子体分离流控制频率优化及涡运动过程分析

doi:10.7527/S1000-6893.2015.0246

Abstract

Abstract:

The nanosecond pulsed plasma discharge actuator is used on a NASA SC (2)-0712 airfoil. At the angles of attack of 15° and 20°, the flow control efficacy of the actuators is tested at a series of Reynolds number conditions. The static pressure test result shows that the actuator has different control effect at different forcing frequencies. By calculating the lift coefficient, the relations between the forcing frequency and lift are determined, which shows that the broadband bandwidth of flow 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, move and evolution. This process brings the separated shear layer dynamic evolution, and thus promotes a dynamic mixing of high/low speed airflow to happen in the separated flow region.

Key words: nanosecond pulses, plasma, separated flow, flow control, vortex, coherent structures

CLC Number:

V211.7

DU Hai, SHI Zhiwei, CHENG Keming, LI Ganniu, SONG Tianwei, LI Zheng. Frequency optimization and vortex dynamic process analysis of separated flow control by nanosecond pulsed plasma discharge[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(7): 2102-2111.

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Frequency optimization and vortex dynamic process analysis of separated flow control by nanosecond pulsed plasma discharge

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