A two-dimensional inlet variable geometry scheme with double passage regulation was put forward. The regulation of inlet compress angle and contraction ratio was achieved by the switch of the downstream compress passage to accommodate wide operation range

and the integrative design with aircraft and combustion was also considered. The investigation shows that

this scheme can reduce the staring Mach number to near the ejector/ramjet mode transition point; the starting Mach number hereto is 2.8; higher total pressure recovery coefficient of 0.62 at coming flow Mach number of 3.0

higher mass flow rate of 0.79 at coming flow Mach number of 3.0

and lower resistance are attained during low coming flow Mach number range (which is reduced to more than 30%)

while the inlet performance during high coming flow Mach number range is unvaried.