This work investigates the thrust coefficient and compensation capability of a permeable nozzle compared to the conventional nozzle at different flight speeds. The numerical simulation results demonstrate that the thrust coefficient of the two nozzles decreases slightly with the increase of flight Mach number. The thrust compensation altitude of the permeable nozzle examined in this work is the same at different flight speeds, spanning from 0 km to 15 km. The thrust compensation capability of the permeable nozzle is altitude-dependent, with the greatest flight speed influence on compensation capability occurring at 5 km. At this altitude, the permeable nozzle demonstrates a greater thrust advantage over the conventional nozzle as the flight Mach number increases.