DEVELOPMENT OF A COUPLING APPROACH FOR SOLUTION OF STATIC AEROELASTIC PROBLEMS

Erkut başkut

ROKETSAN Missile Industries Inc., P.K.:30, 06780 Elmadağ-Ankara-Türkiye, ebaskut@roketsan.com.tr

alİ akgüL

ROKETSAN Missile Industries Inc., P.K.:30, 06780 Elmadağ-Ankara-Türkiye, aakgul@roketsan.com.tr

Abstract: In this study a fluid-structure coupling procedure which consists 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. The flow solver relies on inviscid Euler equations with finite volume discretization. In order to perform faster computations, multiple processors are parallelized. Euler equations and elastic linear structural equations are coupled to predict deformations under aerodynamic loads. Linear interpolation using Alternating Digital Tree data structure is performed in order to exchange the data between structural and aerodynamic grid. In order to adapt the new shape of the aerodynamic surface at each aeroelastic iteration, Computational Fluid Dynamic mesh is moved based on spring based smoothing and local re-meshing method provided by FLUENT moving mesh algorithm. AGARD Wing 445.6 and a generic slender missile are modeled and solved with the developed procedure and obtained results are compared with numerical and experimental data available in literature.