Abstract: The pressure inside and outside of the permeable nozzle can be balanced by driving airflow into and out of permeable section, so as to realize the flow field structure adjustment and adaptive altitude compensation near the wall surface. In order to reduce the performance loss caused by over/under-expansion of traditional rocket nozzle at off-design altitudes and meet the demand of high-efficiency propulsion along the entire trajectory for single-stage-to-orbit missions, the influence of five kinds of perforation geometric shapes in the permeable section on thrust performance of permeable nozzles was investigated via numerical simulation, including cylindrical hole, two kinds of conical frustum hole, square hole and triangular hole. While ensuring the identical porosity and perforation arrangement of the porous plate structure permeable nozzle, five kinds of permeable nozzle models were constructed. The numerical simulation was carried out under typical flight conditions from 0 to 30 km, and the influence of the hole shapes of the permeable nozzle on flow development in the perforation path and mainstream was analyzed. The results show that airflow passes through the openings of the permeable section to form orifice jets, whose expansion level determines the intensity of interaction with the mainstream, thereby affecting the internal flow field structure of the nozzle, the inner wall pressure, and the thrust performance of the nozzle. Under the same flight conditions, perforation structure of the permeable nozzle affects the airflow development inside the path, leading to differences in the expansion degree of the orifice jets. The design of a circular hole-path structure with large outer-wall openings and small inner-wall openings was adopted. The permeable nozzle favors airflow inflow at low altitude and suppresses airflow outflow at high altitude, showing the best altitude compensation ability. Compared with the traditional nozzle, the thrust performance of the cone-shaped hole permeable nozzle is improved by 0.21% within the flight range of 0~30 km.