Nonlinear Aeroelastic Response of the Flexible Wing in Trim

The nonlinear aeroelastic response of a wing constrained by tri m conditions is examined using the method of numerical continuation. A formulation for a wing model ed as a cantilevered beam is used to analyze motion about all axes, including in-plane motion. T he kinematic nonlinearities due to curvature and inertia are retained in their ex act form. An aerodynamic stall nonlinearity is included using a quasi-steady approach. Trim state, stability, and associated bifurcation characteristics are rapidly determined as design pa rameters are varied. Limit cycle oscillations are investigated and are characterized in terms of amplitude of response. The effect of variation of design parameters such as stiffness ratio, aspec t ratio and root angle of attack is studied. Both subcritical and supercritical bifurcation branches are de tected, and the presence is dependent upon design parameters. In particular, the authors examine the importance of the inplane degree of freedom on the stability characteristics of the wing in tri m.

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