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 H? 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

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