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In order to obtain the impact law and mechanism of different degrees of damage in the diffusion section of a certain type of solid rocket motor with a long tail pipe on its performance during operation, CFD method was used to model and simulate it. By comparing the flow field distribution and thrust changes under different degrees of damage, the impact law of nozzle diffusion section damage on the flow field and performance of this type of engine was revealed; Studies have found that the outflow of gas from the gap is basically fan-shaped in the axial section, and there is an angular structure at the intersection of the fan-shaped arc and radius. The isosurface of the flow field can be divided into three parts: the isosurface of the gap, the isosurface of the non-gap and the isosurface of the interaction between them. When the nozzle is damaged in the diffusion section, the downstream flow field will be affected, and the upstream flow field will be very small. With the increase of the gap at the end of the diffusion section, the angle between the thrust direction and the nozzle axis increases continuously.