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.


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    Title :

    Predicting Limit Cycle Oscillation in an Aeroelastic System Using Nonlinear Normal Modes


    Contributors:

    Published in:

    Journal of Aircraft ; 50 , 1 ; 73-81


    Publication date :

    2013-01-01




    Type of media :

    Conference paper , Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English






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