Control of flow separation from an airfoil using piezo-ceramic actuators

Hong J. Zhang, Yu Zhou, Li Cheng

Research output: Chapter in book / Conference proceedingConference article published in proceeding or bookAcademic researchpeer-review

Abstract

THUNDER Piezo-cerarnic actuators were used to suppress boundary layer separation from a NACA0015 airfoil. The actuators generated a small normal-to-surface perturbation near the leading edge of the airfoil. While the flow field around the airfoil was measured using a particle imaged velocimeter, instantaneous lift and drag Forces were obtained using a load cell. The results show that the flow separation can be suppressed or postponed by this perturbation as long as the perturbation frequency is high enough, say higher than 10 times of the dominant frequency of vortex shedding from the airfoil. It was found that the static-stall angle of attack can be extended by 1-2° at the present Reynolds number of 1.2 × 105.
Original languageEnglish
Title of host publicationCollection of Technical Papers - 3rd AIAA Flow Control Conference
Pages1642-1648
Number of pages7
Volume3
Publication statusPublished - 11 Dec 2006
Event3rd AIAA Flow Control Conference - San Francisco, CA, United States
Duration: 5 Jun 20068 Jun 2006

Conference

Conference3rd AIAA Flow Control Conference
Country/TerritoryUnited States
CitySan Francisco, CA
Period5/06/068/06/06

ASJC Scopus subject areas

  • Engineering(all)

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