Improved aeroelastic analysis framework to assess shear and cross-section deformability effects on static aeroelastic response

This research investigates the influence of shear and cross-section deformability on the static aeroelastic response of wings by applying a high-fidelity computational framework that couples Computational Fluid Dynamics (CFD) with refined one-dimensional (1D) and two-dimensional (2D) structural theories based on the Carrera Unified Formulation (CUF). The framework incorporates low- and higher-order beam and plate theories to capture airfoil deformations, utilizing both Taylor and Lagrange expansion functions for the kinematics. Aerodynamic loads from the CFD model are transferred to the structural finite element model via the Infinite Plate Spline (IPS) method. The static aeroelastic response of various wing configurations, differing in aspect ratio, airfoil geometry, and sweep angle, is analyzed to assess aerodynamic loading calculation and the influence of elastic airfoil deformation. Comparisons with reference solutions and Vortex Lattice Method (VLM) results demonstrate the accuracy and reliability of the presented methodology, highlighting the importance of higher-order models for accurate aeroelastic static response of aeronautical wings. The study further demonstrates the stabilizing effects of sweep angles in mitigating aeroelastic instabilities, providing valuable insights for aerospace design. The results establish the framework as a powerful tool for preliminary aircraft design, enabling efficient aeroelastic assessments using efficient 1D finite elements.