  The purpose of this work is to expand the work of Streher (2017) in order to
investigate the aeroelastic instabilities generated by the flow around a moving
NACA0012 airfoil. The profile has a chord length of $c=0.1 m and is exposed to
a flow at a Reynolds number of Re=30,000. The airfoil has only two degrees of
freedom: Translation in relation to the vertical direction and a rotation
around the span-wise axis. A partitioned approach based on two separate solvers
and a fluid-structure interaction (FSI) coupling scheme is applied. The
in-house CFD solver FASTEST-3D computes the fluid sub-problem according to the
wall-resolved large-eddy simulation (LES) combined with the Smagorinsky model
(1963). The structural sub-problem is solved by a rigid movement solver
implemented by Viets (2013), which is based on the equations of motion for
rigid bodies. The FSI coupling exchanges information between both solvers based
on loose or strong coupling algorithms. A thorough analysis of the problem is
primarily performed in order to acquire a computational setup that provides the
best compromise between accuracy and CPU-time requirements. Three system
configurations are then tested and thoroughly investigated: One leads to an
oscillatory behavior of the airfoil characterized by limited small amplitudes.
The other is characterized by the presence of the torsional divergence
aeroelastic instability. Finally, a configuration aimed at the flutter
phenomenon is established. However, not enough data are currently available and
therefore this dynamic aeroelastic instability can not be thoroughly
investigated in the present work. In the near future, this study will serve as
a base for the flutter experiments and computations performed at the Department
of Fluid Mechanics located of the Helmut-Schmidt-University.
