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