Influences of the forebody boundary layer state on shock pattern

characteristics of shock/boundary-layer interaction

mass capture capability and total pressure recovery of axisymmetric hypersonic inlet were studied with the aids of CFD.The performance trend in accordance with the forced transition position was obtained at different Mach numbers.As a forced transition device

two-dimensional roughness was introduced to examine the disturbance it made to the flow field.Differences between specific inlet design schemes were also compared in the study.