The flexibility of the modern aircraft structures paves the way for the study of aero elasticity during the verification procedures of aircraft design and stability. The structures of wing will cautiously vibrate, either linearly or non-linearly due to the coupling effect between the aerodynamic, inertial and elastic forces of the wing structure, so the designing of aircraft involves two major aero elastic considerations such as wing torsional divergence and flutter. However, flutter problems are considered from the field of dynamic stability, the modal representation of flutter analysis is done by setting up the lifting surface as a linear ordinary differential equation, then changed to Eigen values and further stability analysis has been done. In order to complete the flutter analysis as an analytical tool, two important aerodynamic theories are taken into account and we identified and solved the classical flutter derivatives by using Eigen value method and also the position of flexural and mass axis of the simple rectangular wing on flutter speed has been analysed.
Classical flutter analysis of composite wind turbine blades including compressibility
