Unsteady and Post-Stall Model Identification Using Dynamic Stall Maneuvers

The purpose of this work is to identify a high angle of attack model of a turboprop aircraft using data from flight tests. The classic quasi-steady stall maneuver was modified to include elevator inputs during the approach to stall, as an effort to improve the estimation of dynamic derivatives. In order to allow application of Flight Path Reconstruction techniques, additional inputs were applied to the rudder as well, allowing to calibrate the aircraft sensors in all axes. Once the instrumentation errors were obtained, the high angle of attack model identification process was applied to both stall maneuvers separately: the classic quasi-steady stall and the modified dynamic stall, that includes elevator and rudder doublets. During the validation tests, the results showed that the model obtained by the modified maneuver has a better predictive capability than the model obtained using the classic maneuver.