Development of a Closely Coupled Procedure for Dynamic Aeroelastic Analyses

 

Erkut Başkut

Ali Akgül

 

In this paper, a numerical method is developed to predict the aeroelastic response and the flutter boundary of elastic structures. A closely coupled approach is used for time advancing. The flow solver relies on inviscid Euler equations with finite volume discretization. A modal approach is used for a structural response and the Newmark algorithm is used for time marching. In order to exchange displacement and pressure data between structural and aerodynamic grids, the infinite spline method is used. The Computational Fluid Dynamic mesh is moved based on the spring-based smoothing and the local re-meshing method provided by the FLUENT User Defined Function in order to adapt a new shape of the aerodynamic surface at each aeroelastic iteration. The AGARD Wing 445.6 is modeled and solved with the developed procedure. The obtained results are compared with numerical and experimental data available in the literature.

 

Key words: aeroelasticity, dynamic aeroelasticity, wing, flutter, finite element method, algorithm.