Abstract: A corrected panel method is shown and applied to static aeroealsticity.Based on CFD data at different attack angles the method approximates curved lifting lines by linear segment.The corrected panel method fills drawback of original one by considering nonlinear factor.Compared with CFD,similar accuracy limit and higher efficiency are obtained in aerodynamic force loss and attack angle compensation of M6 wing.It indicates that the method is suitable for complex structure optimization.

Key words: static aeroealsticity, corrected panel method, aerodynamic force loss, attack angle compensation