Experiment of a Ma4 chin inlet with mixed-compression had been done

the pneumatic performance of the inlet was obtained.The results showed that: (1) When Ma=3.5

angle of attack and angle of yaw are both 0 degree

the total pressure recovery coefficient increased at first and then decreased with the increasing of back-pressure

the total pressure recovery coefficient got its maximum at the critical state. (2) Under the critical states of angle of attack and angle of yaw are both 0 degree.The total pressure recovery of inlet decreased linearly with the increasing of flight mach number. (3) The inlet performance declined under pitch or yaw conditions. (4) The inlet has restarting character in the unstart process caused by back-pressure

phenomenon of hysteresis is not obtained in the loop from start to restart induced by the back pressure during the mass adjustor moving forward/backward process(AFBP).