Abstract
NASA CRM has been used for evaluation of the effect aeroelasticity on aerodynamic forces and local flowfield. A CFD analysis of the rigid model showed large differences between the CFD and experimental data. It was observed that the model deformation has significant effect on the aerodynamic characteristics. The on-line mesh deformation on basis of a wing modal analysis was used to improve accuracy of CFD results. Twenty modes in total were used during coupled CFD simulations. The results from this simulations showed that adding the wing deformation into the CFD simulation did improve the accuracy of obtained aerodynamic coefficients. The same methodology has been applied to the full model configuration considering the deformation of all parts of the model. The results from the CFD analyses with on-line mesh deformation of the semi-span and full model are the focus of this paper.
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