The M3 aircraft was equipped with a three-dimensional model of a certain type of engine as the research object, and the CFD method was used to carry out numerical calculations on the entire flow field. For the powered nacelle model, the partitioned stitching grid technology was used to mesh and splice the internal and external flow fields of the engine. On this basis, Reynolds Mean Equation (N-S) and S-A turbulence model were used to calculate the flow field of three different Ma, different engine state and different angles of attack. Under the state of FNPR=1.61, the lift and drag fright obtained by the experiment was used as a reference, and the correction factor of the CFD calculation result was obtained under different angles of attack. The results show that the revised numerical calculation results fit well with the lift characteristic curve measured by the wind tunnel test. The error was less than 3% within 14°; The overall trend of the modified resistance characteristic curve was consistent with the wind tunnel test, with an error of less than 10%, and the resistance curves increase the angle of attack, and increase rapidly after the angle of attack, and increase rapidly after the angle of attack was greater than 10°.