Investigating of the Nonlinear Aeroelasticity Behavior of an Airfoil Using a Direct Approach

This paper presents a new approach in the computational aeroelasticity for deriving the equations of a two dimensional airfoil considering the nonlinear heaving and pitching stiffeners for structural modeling and the unsteady airstreams based on the Wagner integral function as aerodynamics loading. In this approach a new form of the equations can be obtained by derivation from the primary nonlinear integro-differential aeroelastic equations. The mentioned equations that are in the form of ordinary differential equations can be solved by the ordinary numeric methods such as Runge-Kutta etc. The obtained results for a test case show good agreement with those of the some other researches.

Keywords:

Aeroelasticity , Limit Cycle Oscillation , Wagner Function , Integro-differential system of equations