In order to improve self-starting performance of the fixed-geometry inlet at low Mach number

a technology of self-adaptive pressure relief slot was proposed.The law about the location

direction and effective area of single adapted pressure relief slot was studied with a high performance two-dimensional hypersonic inlet utilizing the technology of numerical simulation.The result shows that:the slot has little influence on the model inlet

and the total pressure recovery ranges around 2%;the slot located downstream the cowl shock wave has large outgassing rate

which will increase as the angle descends and the effective area ascends.The outgassing rate of the adapted pressure relief slot is just 50% compared with normal slot under the same condition.It will drop as the Mach number increases

approaching self-close state at high Mach number condition.