Induced flow simulation with detailed discharge modeling in dielectric-barrier-discharge plasma actuator

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

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.

Original languageEnglish
Title of host publicationAIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Edition210059
ISBN (Print)9781624105241
DOIs
Publication statusPublished - 2018 Jan 1
EventAIAA Aerospace Sciences Meeting, 2018 - Kissimmee, United States
Duration: 2018 Jan 82018 Jan 12

Publication series

NameAIAA Aerospace Sciences Meeting, 2018
Number210059

Other

OtherAIAA Aerospace Sciences Meeting, 2018
CountryUnited States
CityKissimmee
Period18/1/818/1/12

ASJC Scopus subject areas

  • Aerospace Engineering

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  • Cite this

    Sato, S., Takahashi, M., & Ohnishi, N. (2018). Induced flow simulation with detailed discharge modeling in dielectric-barrier-discharge plasma actuator. In AIAA Aerospace Sciences Meeting (210059 ed.). (AIAA Aerospace Sciences Meeting, 2018; No. 210059). American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2018-1293