Experimental investigation of open- and closed-loop control for airfoil under low Reynolds number conditions

Benjamin Plogmann, Steffen Mack, Hermann F. Fasel

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

33 Scopus citations

Abstract

Airfoils operating under low Reynolds number conditions are susceptible to laminar separation, which can cause significant performance losses. The flow field around a two-dimensional, slightly modified NACA 643 - 618 airfoil was investigated experimentally for a wide range of angles of attack (between -12° and 21°). At chord Reynolds numbers of Re = 64, 200 and Re = 137, 000 and at moderate angles of attack, the airfoil suffers severe performance losses due to large regions of laminar separation on its suction side. Open-and closed-loop flow control strategies were employed to eliminate or at least to significantly reduce laminar separation. When successful, the control resulted in a significant lift recovery and drag reduction. Closed-loop control was found to be equally effective as an optimized open-loop control. The main advantage of the proposed easy-to-implement feedback controller is that it automatically adjusts the unsteady actuation to changing free-stream conditions.

Original languageEnglish (US)
Title of host publication39th AIAA Fluid Dynamics Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Print)9781563479755
DOIs
StatePublished - Jan 1 2009

Publication series

Name39th AIAA Fluid Dynamics Conference

ASJC Scopus subject areas

  • Engineering (miscellaneous)
  • Aerospace Engineering

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    Plogmann, B., Mack, S., & Fasel, H. F. (2009). Experimental investigation of open- and closed-loop control for airfoil under low Reynolds number conditions. In 39th AIAA Fluid Dynamics Conference [2009-4282] (39th AIAA Fluid Dynamics Conference). American Institute of Aeronautics and Astronautics Inc.. https://doi.org/10.2514/6.2009-4282