This paper presented an aerodynamic-structure analysis and evaluation of an airfoil with Continuous Trailing-edge Flap (CTEF) for future application on helicopter blades. CTEF airfoil uses embed piezoelectric-fiber actuators to deform the trailing edge of an airfoil and induces aerodynamic changes. Structural analysis was developed to model the airfoil deformation under both aerodynamic and electric loads. Two open-source codes, XFOIL (panel method) and OpenFOAM (CFD), were used to provide the aerodynamic pressure and evaluate the aerodynamic performance of the CTEF airfoil. Typical Fluid-Structure Interaction (FSI) method was used to couple the structural and aerodynamic analysis for a comprehensive simulation of the CTEF airfoil. The coupled procedure was validated using previous bench test and wind tunnel test data. CTEF displacements were calculated for three actuation voltages: 0 and ± 750V under different wind tunnel velocities. The variation of CTEF displacement with velocity was compared with the test data and showed relatively good agreement. Aerodynamic coefficients of the CTEF airfoil were computed and compared with the wind tunnel test data and showed fair agreement.
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