Abstract: A Caret inlet was studied by testing.Basic aerodynamic characteristics of the inlet at supersonic speed are presented.The total pressure recovery rapidly drops from Mach 1.6 to 2.0.No inlet/engine match point at Mach 2.0 without bypass was found due to the fact that the surge margin happened to be too narrow.Steady circumferential distortion declines from surge to critical state,nevertheless,dynamic turbulence intensity increases rapidly.Flow separations are visible in duct from critical to supercritical states,these separations stem from the intersection of two ramps and low outboard.