Abstract
The purpose of the present paper is to study the flutter instability and forced response of a non-rotating helicopter blade model with a parabolic or cubic and freeplay torsional stiffness non-linearity based upon the semi-empirical (linear and) non-linear ONERA stall aerodynamic model. An experiment has also been carried out in the Duke Universtiy low speed wind tunnel. The wind tunnel test results show good agreement between theory and experiment for linear and non-linear flutter instability; for periodic, limit cycle and chaotic flutter motion and forced response behavior; and for the effects of an initial disturbance on non-linear flutter instability. Comparisons of the results from theory and experiment are helpful in understanding physically the non-linear aeroelasticity phenomena and chaotic oscillations.
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