Aeroelastic analysis method of wings based on Euler equations

The traditional aeroelastic analysis methods (such as the famous NASTRAN) has a lot of defects. A numerical method based on Euler equations is presented to calculate the aeroelastic characteristics of wings in all subsonic, transonic and supersonic flows. The transfinite interpolation method is used to generate the grids around the wing, and a finite volume algorithm based on center difference is used to solve Euler equations. The dual-time scheme is introduced to treat the unsteady aerodynamic problem. The motion equations of elastic wing structure are marched by Runge-Kutta method in the time domain. Both static and dynamic deformations of the wings are considered. The numerical results are in good agreement with the aeroelastic experiments done by authors.