Abstract
The NASA Common Research Model has been used for evaluation of the effect of the deformation of the model on aerodynamic forces and local flowfield. Large differences were observed during comparison of the results of the rigid model and experimental data obtained during ESWIRP project at European Transonic Windtunnel. On-line mesh deformation using 20 modes in total was used during coupled CFD simulations to improve the accuracy of the numerical results. The results from these simulations showed that adding the wing deformation into the computational fluid dynamics simulation improved the accuracy of obtained aerodynamic coefficients and also the local flowfield. The results from the coupled CFD simulation with on-line mesh deformation of the semispan model are the focus of this paper.
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