A high-fidelity static aeroelastic analysis method for complex configuration and its application

For a large transport aircraft with high aspect ratio wing, aeroelasticity is one of the most important factors that affects the aerodynamic efficiency of a high-lift configuration. To analyze its static aeroelasticity accurately, we propose the high-fidelity static aeroelastic analysis method based on the solution of Navier-Stokes equations and structural equations. We develop a global-local mixed algorithm for exchanging data between computational fluid dynamics results and computational structural dynamics results, which eliminates the data interference among adjacent parts of the complex configuration. We also work out the dynamic mesh method that uses the radial basis function interpolation technique that has good elastic deformation and introduces the parallel algorithm, thus guaranteeing the mesh deformation capability of the complex configuration. In order to enhance the static aeroelastic analysis efficiency, we introduce the convergence acceleration technique based on the convergence characteristics. Finally, we use the DLR-F6 wing body configuration and the high-lift configuration of a large transport aircraft to verify the feasibility and robustness of the static aeroelastic analysis method. The verification results show that the elastic deformation decreases the lift coefficient of the high-lift configuration results by around 1.0% under the influence of aeroelasticity.