Abstract
The paper deals with the study of an analytical model of wing rock, based on parameter identification of experimental data. The experiments were performed in the Aeronautical Laboratory of Politecnico di Torino, in the D3M Low Speed Wind Tunnel, on a 80∘ delta wing with a modular fuselage, designed with a cylindrical forebody and a conical nose tip. Free-to-roll tests have been used to determine build up and limit cycle characteristics of wing rock. An analytical nonlinear model was derived. Parameters were identified by means of least squares approximation of experimental data with coherent initial conditions. The consistency of time histories, reproduced by numerical integration, was also analyzed. This formulation correctly predicts stable limit cycles for a wide range of airspeeds, angles of attack, and release roll angles. Finally, the impact of aircraft configuration on wing rock parameters is here outlined.
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