Mauwafak A. Tawfik; Mohammed I. Abu-Tabikh; Hayder S. Abd Al-Amir
Abstract
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 ...
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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 design.
