This paper presents a practical workflow on static aeroelastic problems with extreme deflections. The aim of this study is to achieve a fast, yet robust method to calculate the change of the aerodynamic parameters as well as to ensure structural integrity of a wing deforming under aerodynamic loads. To predict static aeroelastic behavior of a high aspect ratio wing, calculations are performed on very fine grids at a relatively large number of flight conditions. Fluid calculations are performed with FLUENT on viscous meshes containing highly skewed cells, while structural analysis is performed by MSC.NASTRAN on 10-noded tetrahedral meshes. Aerodynamic loads on a wing surface are transferred to structural analysis and deformations are transferred to aerodynamic analysis to repeat the aerodynamic calculations. This iterative process between the aerodynamic analysis and structural analysis is continued until a convergence criterion is met. Deformation of the wing surface is transferred to the fluid mesh using spring analogy. In order to achieve high quality fluid meshes after deformation and to reduce calculation time different methods are used. As the basis of the spring analogy, segment springs and ball vertex methods are utilized. Then, to reduce computer time, a SOR type solver and a layered solver are employed. Last improvement involves an initial guess of the deformations inside fluid mesh. As a result, we manage to perform static aeroelastic calculations on the wing geometry in a reasonably shorter time. © 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.