Limit cycle behavior has been observed in past transonic flutter calculations by the authors, using a two degree of freedom typical section model coupled to an unsteady Euler equation solver. In this article, the structural nonlinearity of freeplay has been added to the typical section model, and its effects on the dynamic stability problem are assessed. In addition, limit cycle behavior in the swept wing model of Isogai is demonstrated and related to the observed presence of multiple flutter points in the transonic dip region
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Kousen et al. (1994) studied this question.
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