The Aeroelastic analysis is traditionally done in frequency domain and in time domain, state space frame-work. In this paper, this analysis is carried out in time domain matrix second order form. This way, the physical insight is preserved, thereby handling the problems associated with strongly interacting aeroelastic systems more effectively. A two-dimensional "typical airfoil section" model is considered under steady flow and quasi-steady flow and preliminary stability analysis is carried out in matrix second order framework. Simple sufficient conditions for avoiding flutter occurrence in given flight envelope are given, which if satisfied, can eliminate the need for cumbersome numerical procedure. Moreover, the conditions are explicitly in terms of physical parameters (mass, damping, stiffness etc) of the system, which is very helpful in designing the system.
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