Control of dynamically stalled flowfield around a pitching airfoil by DBD plasma actuator

Hiroaki Fukumoto, Hikaru Aono, Motofumi Tanaka, Hisashi Matsuda, Toshiki Osako, Taku Nonomura, Akira Oyama, Kozo Fujii

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

4 Citations (Scopus)


Effects of plasma actuator on the dynamically stalled flowfield with Re = 2.56×105 around a pitching NACA0012 airfoil have been investigated by large-eddy simulations (LESs) with sufficient computational spanwise domain length. The dynamically stalled flowfield is characterized by laminar separation bubble, dynamic stall vortex and fully separated flowfield and the current LESs show good agreements with the experimental results with and without plasma actuator. With plasma actuator, the lift coefficient CL during the pitching down is significantly enhanced by the induced large leading edge vortex, whereas the drag coefficient CD is also increased.

Original languageEnglish
Title of host publication8th AIAA Flow Control Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624104329
Publication statusPublished - 2016
Externally publishedYes
Event8th AIAA Flow Control Conference, 2016 - Washington, United States
Duration: 2016 Jun 132016 Jun 17

Publication series

Name8th AIAA Flow Control Conference


Other8th AIAA Flow Control Conference, 2016
Country/TerritoryUnited States

ASJC Scopus subject areas

  • Fluid Flow and Transfer Processes
  • Control and Systems Engineering
  • Aerospace Engineering


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