Aeroelasticity problem solution by use of fem variables

The technique of flutter/divergence speed calculation of airplane wing on the basis of its FEM model is proposed. Aerodynamic loadings are defined by a panel method and transferred on FEM model. For research of stability bounds of aeroelastic oscillations the dynamic reduction of FEM system equations is made. The technique is realized in the form of the program module for the personal computer. The calculation example is given