Abstract: With the development of aircraft airworthiness noise strictness requirements, it has become an effective strategy and research direction to use wing shielding effect to control aircraft engine noise. In this paper, based on Huygens Fresnel principle, aircraft noise and performance (ANP) database is used to calculate the aircraft take-off track and establish noise sources on it. The sound source position is taken as the coordinates for noise shielding calculation coordinate to input the shielding effect algorithm. The mathematical modeling software (Matlab) is used to model the direct sound field and the diffractive sound field of noise transmission, and the sound pressure level shielded by wing is calculated and analyzed by insert loss of wing barrier. The results are combined with the Heidmann fan noise prediction model to evaluate the effect of noise shielding on fan noise. Compared with the prediction results of fan forward noise with or without wing shielding effect, it is found that the effect of wing shielding increases first and then decreases with the movement of noise propagation path from the leading edge to the trailing edge of the wing, and the higher the noise frequency, the more obvious the shielding effect is.