This paper demonstrates the use of nonlinear normal modes to predict limit cycle oscillation in a pitch-plunge airfoil with cubically nonlinear pitch stiffness. Aeroelastic systems with quasi-steady and unsteady aerodynamics are analyzed with nonlinear normal modes. An alternative derivation of nonlinear normal modes using first-order form is offered for systems that cannot fit the standard second-order form. The effect of the master coordinate chosen to construct the nonlinear normal modes is examined and found to have a significant impact on the accuracy of the results. Based on the results herein the nonlinear normal mode method is found to be a viable approach to studying and predicting limit cycle oscillation in aeroelastic systems. Furthermore, a master coordinate based on the the linear flutter mode was found to lead to the best results.
Predicting Limit Cycle Oscillation in an Aeroelastic System Using Nonlinear Normal Modes
Journal of Aircraft ; 50 , 1 ; 73-81
2013-01-02
9 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Predicting Limit Cycle Oscillation in an Aeroelastic System Using Nonlinear Normal Modes
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