Abstract: A loosely-coupled procedure for static aeroelasticanalysis of a flying wing is presented. Firstly, the flow solvers used arebased on an Euler model and a RANS model with structured grid, and an Eulermodel with unstructured grid. Secondly, the structure modal analysis andflexibility matrix method are all applied. Furthermore, a theoretical caseof the flying wing is carried out in cruise condition of Mach number of 0.6and the angle of attack of 2? at 20km altitude. The results show thatthe flexibility matrix method is more suitable for static aeroelasticanalysis than the structure modal analysis. Meanwhile, a surface deflectionmethod is validated to be more efficient than the grid deformation method inthe computation analysis due to the three-dimensional geometriesdeformation.