Experimental study on detailed structure of separation bubble in controlled flow by DBD plasma actuator around airfoil

Yuma Miyakawa, Satoshi Sekimoto, Makoto Sato, Taku Nonomura, Akira Oyama, Kozo Fujii, Shinichiro Ito

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

Abstract

This study focuses on detailed structures of a separation bubble in controlled airfoil-flows using a DBD plasma actuator. Time-averaged surface pressure measurements and well-resolved PIV are conducted. The present PIV measurement enables the observation of the detailed flow structure near the leading edge by connecting three adjacent images of particle image velocimetry (PIV). The airfoil is NACA0015 and the Reynolds number based on the chord length is 63,000. The angle of attack is 12 deg. corresponding to the fully separated flow from the leading edge. Three types of actuation (the normal-mode case mode and burst modes with F+ = 1 and 6 ) are considered. The flow control mechanism related to a separation bubble is discussed for each case through time-averaged and phase-averaged flow fields.

Original languageEnglish
Title of host publication47th AIAA Fluid Dynamics Conference, 2017
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105005
Publication statusPublished - 2017
Event47th AIAA Fluid Dynamics Conference, 2017 - Denver, United States
Duration: 2017 Jun 52017 Jun 9

Publication series

Name47th AIAA Fluid Dynamics Conference, 2017

Other

Other47th AIAA Fluid Dynamics Conference, 2017
CountryUnited States
CityDenver
Period17/6/517/6/9

ASJC Scopus subject areas

  • Aerospace Engineering
  • Engineering (miscellaneous)

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