Abstract
The application of the finite element method to the solution of static and dynamic aeroelasticity problems is presented. The approach is quite general and is applicable to any lifting surface type structure with arbitrary configuration, which might have cutouts and other structural discontinuities. By using the natural mode shapes as the generalized coordinates, the necessary matrix equations are derived from Lagrange's equations. The aerodynamic matrices are obtained from piston theory and also from a quasi-steady form of a theory for two-dimensional steady flow. Numerical examples are presented to illustrate the application of the method in the solution of load distribution and flutter problems.