Large-attack-angle nonlinear separation flow aerodynamic force correction method

**The invention discloses a large-attack-angle nonlinear separation flow aerodynamic force correction method. The method comprises the following steps: obtaining aircraft surface pressure distribution data under zero reduction frequency by adopting a DES (Data Encryption Standard) method; performing surface element division on the surface area of the aircraft, and generating an AIC matrix AIC by adopting a dipole grid method based on geometric information of each surface element; the aerodynamic force and the torque of each surface element are obtained according to the AIC, the aerodynamic force and the torque of each surface element are utilized to generate an aerodynamic force matrix ADLM of all surface elements under the zero reduction frequency, and k is equal to 0; interpolating aircraft surface pressure distribution data obtained by adopting a DES method to each surface element to obtain an aerodynamic matrix ADES of all the surface elements; obtaining a force correction matrix W according to ADLM, k =