Aeroelastic oscillations of a pitching cantilever wing with structural geometric nonlinearities: theory, numerical simulation and global sensitivity analysis
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The focus of this thesis is the aeroelastic dynamics of a rectangular cantilever wing with a NACA 0012 profile, whose base is free to rotate rigidly about a longitudinal axis. The wing is analytically modelled as part of a project to simulate the dynamics of an aeroelastic wind tunnel model. Structural geometric nonlinearities capture the essential effects of large deformation. The derivation closely follows common approaches from the literature, however new inertial terms arise from the kinematics of the added rigid body degree of freedom in pitch. Using an unsteady linear aerodynamics model, it is observed that the system undergoes coalescence flutter. The post-flutter behaviour is dictated by the structural geometric nonlinear terms which limit the oscillations to a limit cycle. Global sensitivity analysis is performed to study the effect of parametric uncertainty introduced by the rigid body base rotation on the flutter speed and associated frequency.
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Copyright © 2018 the author(s). Theses may be used for non-commercial research, educational, or related academic purposes only. Such uses include personal study, research, scholarship, and teaching. Theses may only be shared by linking to Carleton University Institutional Repository and no part may be used without proper attribution to the author. No part may be used for commercial purposes directly or indirectly via a for-profit platform; no adaptation or derivative works are permitted without consent from the copyright owner.
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robinson-aeroelasticoscillationsofapitchingcantilever.pdf | 2023-05-05 | Public | Download |