To enable the flight of turbo/ramjet combined cycle engine within extensive altitude and speed

the aerodynamic structure of a variable geometry inlet for combined cycle engine was designed in this paper.Estimation program of shock structure with viscous correction was compiled to estimate the shock structures and intensities in the inlet under different Mach numbers and attack angles.The choice of the variable panel length was governed by the program.Considering the boundary layer suction

two-dimensional flow fields of the inlet were simulated from Mach number 1.6 to 4.0 at attack angles of -2°

0°

+2°.The structures of the flow fields were consistent with the computed results by the compiled program.Aerodynamic characteristics of the variable geometry inlet were acquired.The influences of Mach numbers and attack angles on the adjustment rules and aerodynamic characteristics of the inlet were analyzed.