Abstract: A numerical simulation based on CFD/CSD method has been carried out to study the transonic static aeroelastic problems of large transporters. The specific methods are described as follows:the Reynolds-averaged Navier-Stokes equations (RANS) and the static aeroelastic balance equation are employed as the governing equations to conduct coupling iterative computation; a multi-block structured grid is generated for parallel CFD computation, and a multi-grid technique is adopted to accelerate convergence; the dynamic mesh generation is completed through the RBF combined with the TFI method; a three-dimensional thin plate spline interpolation technique is adopted to execute the data interchange between the flow field and structure. Based on the above methods and typical wind tunnel test data, a series of codes are developed and validated, and the results indicate the effectiveness of the methods. Finally, the deformation characters, the pressure distribution, and the aerodynamic performance of a typical large transporter's wing are analysed on the basis of the numerical results.