For improving the performance of an integrated wave-rider inlet

the arc tangent Mach number basal flow and enhanced osculating axisymmetric control lines were adopted in the design process. Numerical simulation was conducted at on-design and off-design conditions and flow characteristics were analyzed respectively. At the design condition

the wave-rider inlet had excellent performance and the characteristic of forebody/inlet integration

however

the cross-flow phenomena appeared in the boundary-layer of compression surface as a result of cutting off. At different angles of attack

the configurations of leading edge shock were nearly the same

helping to enhance the flow capture capability at off-design conditions. For different angles of sideslip

the regularity of the performance varying with angle of sideslip was nonlinear as a result of flows ununiformity. A low-pressure region appeared at the leeward side of inner compression part

leading to a stream wise vortex. As the gas flowed to the low-pressure region on different slices

a dual-vortex structure was formed at the inner compression part. As the gas flowed out of low-pressure region

the second vortex was dissipated.