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Flow Control on Gö 387 Airfoil by Using Nanosecond Pulse Plasma Actuator

  • Kentaro KatoEmail author
  • Christian  Breitsamter
Conference paper
Part of the Fluid Mechanics and Its Applications book series (FMIA, volume 107)

Abstract

Airfoil flow separation control using a plasma actuator driven by repetitive nanosecond pulse voltage was experimentally investigated. The pressure distribution on the airfoil surface was measured by means of a liquid manometer. The lift coefficient was computed by integrating the pressure distribution and the effects of the input voltage amplitude and repetitive frequency were evaluated. The results show the lift is increased in two ranges of angle of attack. The first range corresponds to the pre-stall and stall angle of attack. In this range the flow is steady and the lift is increased regardless of the frequency. Strong hysteresis effect is also observed. The second range corresponds to the post-stall angle of attack. In this range the flow is unsteady and the lift increment is heavily dependent on the amplitude and frequency. Characteristic pressure distribution and shift of the separation point, which was estimated from the pressure gradient, are also reported.

Keywords

Pressure Distribution Lift Coefficient Nanosecond Pulse Plasma Actuator Airfoil Surface 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

Notes

Acknowledgments

This work was supported by Erasmus Mundus action 2 project “BEAM Build on Euro Asian Mobility” and also was achieved as an international internship program for COE Research Assistant of Keio University Global Center of Excellence Program “Center for Education and Research of Symbiotic, Safe and Secure System Design”. We appreciate the offers of electric devices from FID GmbH. We wish to acknowledge valuable discussions with Mr. G. Correale and Dr. M. Kotsonis. We would like to thank Dr. Y. Oyamada for the suggestion related to photogrammetric technique.

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Copyright information

© Springer International Publishing Switzerland 2015

Authors and Affiliations

  1. 1.Lehrstuhl für Aerodynamik und StrömungsmechanikTechnische Universität MünchenGarching bei MünchenGermany

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