Abstract: The viscous laminar flow in the inlet is simulated by solving compressible Navier-Stokes equation. The partial differential equations are approximated by CSCM (Conservative Supra - Characteristics Method). The problems of the interaction among the shock wave systems and the interaction between shock and boundary layer in the inlet are researched. The computed results are compared with experiment results. The influences of Mach number in the flow can be seen in the computed results. The smaller Mach number is, the larger the shock angle in the inlet. The shock waves become weak with twice intersections and one reflection. The Reynold number also influences the flow in the inlet. The results of separation in boundary layer due to the interaction between shock and boundarv are obtained.

Key words: computational aerodynamics, shock wove, inlet