The reverse design method of curved compression inlet with controllable internal and external compression surfaces was studied

the numerical simulation and experimental study of the designed 2D curved compression inlet starting with varying angle of attack at different Mach numbers were carried out

and the hysteresis loop of the inlet starting angle of attack was obtained. Simulation and experiment indicated that unstarting/self-starting angle of attack

the outflow field and pressure distribution coincided well

and the experiment results also showed that curved compression inlet had high comprehensive aerodynamic characteristics; at design points Ma=4

α=3° back pressure resistance ability was more than 70 times of inflow pressure

total pressure recovery coefficient was above 0.5.