Closed-Loop Dynamic Stall Control Using Plasma Actuation and Trailing Edge Pressure Sensing for Goman-Khrabrov State Prediction

A dynamically pitched wing is subjected to closed-loop control of a leading-edge plasma actuator in order to study the effects of flow separation and attachment on leading and trailing edge pressure sensors. Controller development is then applied using the Goman-Khrabrov model to attempt state estimation of the degree of separation on the wing using the trailing edge pressure as feedback to the system. The resulting trailing edge pressure-based Goman-Khrabrov predictions were compared to the measured data for unsteady cases and showed good agreement to the trends and magnitudes of lift coefficient.