For flying wing, high aspect ratio low Reynolds number aerodynamic layout is easy in a small angle of attack occurs under conditions of flow separation, it will bring significant nonlinear aerodynamic problems, while the impact of aeroelastic problem also can not be ignored. For this type of layout presents a radial basis function interpolation to establish the non-linear pressure coefficient distribution model. Established by radial basis function interpolation surface element on the angle of attack on the pressure coefficient derivative response surface, the pressure coefficient points and through infinite plate spline (IPS) method of interpolation of multiple iterations to achieve aerodynamic structure nonlinear aeroelastic analysis. The results show that the method for static aeroelastic analysis of the effectiveness of flexibility while accurately reflect bring aerodynamic efficiency loss and distortion effects on lift and drag.