Limit cycle behavior of an airfoil with a control surface

A three-degree-of-freedom aeroelastic model with freeplay is modeled theoretically using a small number of aerodynamic eigenmodes (i.e. a reduced order model) based upon Peters' finite-state model for two-dimensional aerodynamic flow. The limit cycle behavior and the sensitivity to initial conditions for the onset of limit cycle oscillations are discussed. A simple and interesting physical explanation for this behavior is presented based on harmonic balance or describing function calculations that have been confirmed by numerical time simulations. The theoretical results are also in good agreement with experiment and a universal scaling law for the dependence of limit cycle oscillations and bifurcation parameters on freeplay is elucidated. © 1998 Academic Press.

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Author Earl H. Dowell Thomas Lord Department of Mechanical Engineering and Materia ...

Author Lawrence N. Virgin Thomas Lord Department of Mechanical Engineering and Materia ...