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.