This work couples a Vortex Lattice Method, VLM, to a refined one-dimensional structural model based on Carrera Unified Formulation, CUF. Airfoil in-plane deformation and warping are introduced by enriching the displacement field over the cross-section of the wing. Linear to fourth-order expansions are adopted and classical beam theories (Euler-Bernoulli and Timoshenko) are obtained as particular cases. The VLM aerodynamic theory is coupled via an appropriate adaptation of the Infinite Plate Spline method to the structural finite element model. A number of wing configurations (by varying aspect ratio, airfoil geometry, dihedral, and sweep angle) and load cases are analyzed to assess both the calculation of aerodynamic loadings and the influence of in-plane airfoil deformation to the static response of the wing. Comparison with shell results of commercial software such as MSC Nastran, which is taken as reference solution, is carried out and discussed. The importance of higher-order models for an accurate evaluation of local and global response of aircraft wings is shown.