The flow field structure and starting characteristics of two-dimensional inlet/internal flowpath for an airbreathing hypersonic vehicle was analyzed using Ma∞=7 wind tunnel test method.The experimental results show that:if the inlet flowpath is started under incoming total pressure(0.5～1.9 MPa) and unit Reynolds number(2.48×106～7.95×1061/m)

the variation of the incoming total pressure and Reynolds number has little effect on the static pressure distributions along inlet/internal flowpath;the inlet-isolator could withstand maximum back pressure 250 times the free-stream static pressure

before flow in the inlet compression section is disturbed;the inlet has a self-starting ability if no lateral plate is added

and the outlet pressure at the isolator increases if lateral plates are added before the cowl;under the working condition at the design point

the inlet flowpath has a compression ratio 42.9

total pressure recovery of 0.27

and mass-weighted average Mach number of 2.76.