Transonic aeroelastic simulations of aircraft wings

The flutter instability occurring at low speeds in the transonic regime must be accurately predicted and eliminated from the aircraft's flight envelope. In this regime, classical flutter methods are insufficient for flutter prediction because they do not consider nonlinear aerodynamic effects. In recent years, depending on the development of computer technologies, many studies have been carried out to develop methods that calculate the dynamic aeroelastic behavior of the aircraft and the transonic flutter instability limits with sufficient accuracy. With a similar motivation, a method has been developed in this thesis, based entirely on the use of open-source programs to predict flutter instability occurring in the transonic regimen. In this method, a fluid-structure interaction system is established which couple open source computational fluid dynamics (CFD) and computational structural dynamics (CSD) programs. CFD-CSD programs are coupled by strong coupling method using PreCICE coupling library The SU2 program was used to solve the fluid system using CFD methods, and the CalculiX program was used to solve the structural equations. In the simulation process, all of which are open source programs, GMSH for geometry and mesh, and PARAVIEW open source applications are used for displaying the results. Using the generated coupling system, transonic aeroelastic simulations for 2-dimensional and 3-dimensional wing models were performed. The wing models for which aeroelastic simulations were performed are the NACA 64A010 profile (Isogai wing) and Goland+ wing models, which are validation problems in the literature. The instability limits for both wing models were determined, the studies in the literature were compared and the compatibility of the results was discussed.