This article presents a methodology for the detailed sizing of a composite materials aircraft wing subject to wind tunnel testing design requirements. Aiming at the comparison among the numerical and experimental models in terms of structural response, a ground testing campaign has also been conducted. The present wing, designed and manufactured within the scope of the GRETEL project, consists of several internal, external and interface components, since provision is being made for a wind tunnel test campaign. The Finite Element Method (FEM) modeling technique for all the relevant parts of the wing is initially provided, taking into account the boundary conditions as well as the externally applied aerodynamic loads. The sizing methodology and subsequent compliance of the relevant parts and their connectivity elements with respect to design requirements is also explored in detailed fashion. Certain manufacturing requirements and aspects are also manifested and discussed. Following an introduction on the ground testing facilities and measuring equipment, the results of the static tests and the Ground Vibration Testing (GVT) are compared with the corresponding numerical values. Overall, the numerical and experimental results, in terms of displacements, natural frequencies and eigenmodes are in close agreement.
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