10.30684/ etj.29.7.6


The influence of trailing edge flap angle on the aeroelastic behavior of a vibrating
wing-flap configuration is investigated in this work. For this purpose an aeroelastic
numerical model with fully coupled structure-fluid interaction is developed. The flow
and structural solvers are coupled via successive iterations within each physical time
step. The aerodynamic model is based on a hybrid unsteady panel method which is still
a good approach to calculate the unsteady loads. While the nonlinear plate equation
solved by an assumed mode method is used to represent the structure wing model. The
results for a vibrating rectangular wing-flap configuration in low subsonic attached
flow are presented, including the effect of flap angle on the unsteady pressure
coefficient, time history of lifting coefficient and aeroelastic behavior of the wing.
These results clearly show the effect of strong structure-fluid interaction and illustrate
the utility of the present model which may be used in the preliminary stage of the wing