In order to validate fluid-structure interaction solvers, a one degree of freedom
(1 DOF) aeroelastic experiment is performed. A rigid wing with an harmonically actuated
flap, is suspended by springs to allow a free heaving motion. Displacements and time
dependent aerodynamic forces are measured for reduced flap frequencies ranging from k =
0.1 to k = 0.3. Simulations with three codes of different complexity level are performed
for validation purposes: theodorsens model, a 2D panel code and 2D URANS, all coupled
to a 1 DOF structural model. Results presented by bode diagrams, show differences in
both the displacement and the lift between numerical work and experiment. Although
there is an offset, consistency is found between displacements, forces and phase angles in
the system for all simulations and the experiment
