TY - GEN
T1 - Induced flow simulation with detailed discharge modeling in dielectric-barrier-discharge plasma actuator
AU - Sato, Shintaro
AU - Takahashi, Masayuki
AU - Ohnishi, Naofumi
N1 - Funding Information:
The computations in this work were performed on Silicon Graphics International (SGI) Altix UV1000 at Advanced Fluid Information Research Center, Institute of Fluid Science, Tohoku University and FUJITSU Supercomputer PRIMEHPC FX100 at Japan Aerospace Exploration Agency (JAXA). The present work was supported in part through the Program for Leading Graduate Schools, “Inter-Graduate School Doctoral Degree Program on Global Safety” by the Ministry of Education, Culture, Sports, Science and Technology.
Publisher Copyright:
© 2018 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
PY - 2018
Y1 - 2018
N2 - The flow field induced by a dielectric-barrier-discharge (DBD) plasma actuator is complicated because the electrohydrodynamic (EHD) force depends on the applied voltage waveform and the electrode configuration. In this study, fluid-discharge coupling simulation was performed to reproduce the induced flow field driven by the DBD plasma actuator in the atmospheric pressure. The induced flow structure was reproduced with the detailed discharge simulation when a DC-voltage combined with repetitive nanosecond pulses was applied. The DC voltage generates a large EHD force at the beginning; however, the EHD force decreases with time because the electric field is screened due to the surface charge accumulation. The negative pulse voltage ignites a pulsed discharge and neutralizes the dielectric surface, which is positively charged during the DC phase, forming a two-stroke charge cycle. This operation method repetitively generates a large EHD force. A wall jet parallel to the dielectric surface is induced with the two-stroke charge cycle operation. The peak velocity is approximately 4 m/s when the 8-kV DC voltage combined with the -8 kV nanosecond pulses is applied. Shock waves are also repetitively generated due to the fast gas heating at the exposed electrode tip during the pulse superposition phase.
AB - The flow field induced by a dielectric-barrier-discharge (DBD) plasma actuator is complicated because the electrohydrodynamic (EHD) force depends on the applied voltage waveform and the electrode configuration. In this study, fluid-discharge coupling simulation was performed to reproduce the induced flow field driven by the DBD plasma actuator in the atmospheric pressure. The induced flow structure was reproduced with the detailed discharge simulation when a DC-voltage combined with repetitive nanosecond pulses was applied. The DC voltage generates a large EHD force at the beginning; however, the EHD force decreases with time because the electric field is screened due to the surface charge accumulation. The negative pulse voltage ignites a pulsed discharge and neutralizes the dielectric surface, which is positively charged during the DC phase, forming a two-stroke charge cycle. This operation method repetitively generates a large EHD force. A wall jet parallel to the dielectric surface is induced with the two-stroke charge cycle operation. The peak velocity is approximately 4 m/s when the 8-kV DC voltage combined with the -8 kV nanosecond pulses is applied. Shock waves are also repetitively generated due to the fast gas heating at the exposed electrode tip during the pulse superposition phase.
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U2 - 10.2514/6.2018-1293
DO - 10.2514/6.2018-1293
M3 - Conference contribution
AN - SCOPUS:85141559347
SN - 9781624105241
T3 - AIAA Aerospace Sciences Meeting, 2018
BT - AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Aerospace Sciences Meeting, 2018
Y2 - 8 January 2018 through 12 January 2018
ER -