Development of a Coupling Procedure for Static Aeroelastic Analyses

 

Erkut Başkut

Ali Akgül

 

In this paper, a fluid-structure coupling procedure consisting of a commercial flow solver, FLUENT, a finite element structural solver, MSC/NASTRAN, and the coupling interface between the two disciplines is developed in order to solve static aeroelastic problems. Inviscid Euler equations with finite volume discretization are used for the flow solver. Multiple processors are parallelized in order to perform faster computations.  In order to transfer the pressure and displacement data between the structural grid and the aerodynamic one, the Linear interpolation using the Alternating Digital Tree data structure is performed. The Computational Fluid Dynamic mesh is moved based on spring-based smoothing and the local re-meshing method provided by the FLUENT moving mesh algorithm in order to adapt the new shape of the aerodynamic surface at each aeroelastic iteration. The AGARD Wing 445.6 and a generic slender missile are modeled and solved with the developed procedure while the obtained results are compared with numerical and experimental data available in literature.

 

Key words: aeroelastic, static aeroelastic, wing, missile, finite element method, algorithm.