A correction panel method was presented and applied to calculate the aerodynamic center location which is an important parameter in static aeroelasticity problem. The method which based on the CFD data at different attack angle corrected the downwash of the elastic deformation sectionally. Correction panel method fills the drawback of the panel method by including the nonlinear factor. Taken m6 wing aerodynamic center calculation as examples, this method keep high accuracy as well as CFD but performance higher efficiency. The method can get the aerodynamic center location and the aerodynamic center location changes correctly which the traditional panel method cannot handle. This slope corrected method is suitable for design stage of structure project.