Nonlinear Aeroelastic Response of the Flexible Wing in Trim
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abstract
The nonlinear aeroelastic response of a wing constrained by trim conditions is examined using the method of numerical continuation. A formulation for a wing modeled as a cantilevered beam is used to analyze motion about all axes, including in-plane motion. The kinematic nonlinearities due to curvature and inertia are retained in their exact form. An aerodynamic stall nonlinearity is included using a quasi-steady approach. Trim state, stability, and associated bifurcation characteristics are rapidly determined as design parameters 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, aspect ratio and root angle of attack is studied. Both subcritical and supercritical bifurcation branches are detected, 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 trim.
