Investigation of the experimental active control of a typical section airfoil using a trailing edge flap


Journal Article

This paper presents an experimental implementation of an active control system used to suppress flutter in a typical section airfoil. The H2 optimal control system design is based upon experimental system identifications of the transfer functions between three measured system variables: pitch, plunge, and flap position and a single control signal which commands the flap of the airfoil. Closed-loop response of the airfoil demonstrated gust-alleviation below the open-loop flutter-boundary. In addition, the flutter boundary was extended by 12.4% through the application of active control. Cursory robustness tests demonstrate stable control for variations in flow-speed of ±10.

Duke Authors

Cited Authors

  • Vipperman, JS; Clark, RL; Conner, M; Dowell, EH

Published Date

  • January 1, 1997

Published In

Volume / Issue

  • 1 /

Start / End Page

  • 180 - 189

International Standard Serial Number (ISSN)

  • 0273-4508

Citation Source

  • Scopus