The invention provides a reverse aerodynamic performance evaluation method for a
fan blade. The method comprises the following steps: S1, establishing blade appearance
point cloud data; s2, extracting a cross section airfoil profile and geometric parameters: intercepting a cross section to obtain a cross section airfoil profile under the cross section; s3, section
feature recognition and normalization: calculating the chord length and torsion of the cross section; the section airfoil is normalized under the unit chord length and the horizontal chord line reference, and a
point set is obtained; s4,
Fourier descriptor calculation: obtaining Fourier descriptors F corresponding to each section airfoil; S5, airfoil matching and pneumatic epipolar reconstruction; S51, performing similarity calculation on the descriptors corresponding to each section airfoil and descriptors in an airfoil
database, obtaining a
minimum distance airfoil, judging whether the
minimum distance airfoil meets a set matching condition or not, if the
minimum distance airfoil meets the set matching condition, judging whether the minimum distance airfoil meets the set matching condition, and if the minimum distance airfoil meets the set matching condition, performing airfoil matching and pneumatic epipolar reconstruction; and if matching succeeds, directly calling an airfoil profile pole table in an airfoil profile
database, and if matching fails, solving the use value of the airfoil profile of the section, and calculating the pneumatic polar line of the airfoil profile.