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DEVELOPMENT OF A CLOSELY COUPLED APPROACH FOR SOLUTION OF DYNAMIC AEROELASTIC PROBLEMS
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
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Abstract: In this study, a closely coupled approach is used to solve the dynamic aeroelastic problems. To achieve this, a numerical method is developed to predict the aeroelastic response and flutter boundary. The flow solver relies on inviscid Euler equations with finite volume discretization. Modal approach is used for structural response and Newmark algorithm is used for time-marching. Infinite spline method is used to exchange displacement and pressure 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 User Defined Function. AGARD Wing 445.6 is modeled and solved with the developed procedure and obtained results are compared with numerical and experimental data available in literature.
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