Novel Approach of Airfoil Shape Representation Using Modified Finite Element Method for Morphing Trailing Edge

This study presents a novel approach to parameterize the geometry of morphing trailing-edge flap that allows its aerodynamics be optimized while capturing expected structural behavior flap. is based on finite frame element method, whereby initial surface defined as structure with constraints are similar those passive skin. The shape modified by placing series distributed loads surface. method rigid rotation corrections maintain length without requiring nonlinear calculations and achieve accurate surface-length results only solving linear FEM equations twice. proposed enables flaps rapidly formulated maintaining upper angle. inherently integrated into algorithm, eliminating need for unnecessary feasibility checks during aerodynamic optimization. By using airfoil parameterization case was conducted genetic algorithm optimize lift-to-drag ratio NACA 23012 starting at 0.7c 10 degrees deflection. optimizer resulted in structurally feasible achieved 10% increase angle attack range.