Abstract
In this paper, a simulation method was realized to predict aeroelastic response and characteristic parameters of wing structure. This method was developed base on interaction between Fluent solver and Mechanical APDL solver using a coupling system in ANSYS Workbench. AGARD 445.6 wing model was chose for this developed procedure at high speed. Obtained results were compared to other numerical result and experimental results. After that, experiment was also setup in suitable conditions to study aeroelacticity characteristics and specify quantitative parameters as frequency, amplitude of oscillation, wing root forces. Final goal was comparison between numerical results and experimental results on the same wing structure at low speed.
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