In a hypersonic inlet, the incoming flow is compressed through a series of oblique shocks. The shock waves interact with the boundary layer that forms on the inlet wall, which can cause flow separation. Separation bubbles act as blockage in the inlet duct and can result in problems in starting and high localized heat transfer rate. In three-dimensional configuration, the shock/boundary-layer interaction (SBLI) and resulting flow separation can be quite complex. It is important to understand the flow physics in detail, so as to explore ways of minimizing flow separation and its adverse effect. An extensive amount of research has been done on three-dimensional SBLI. The most fundamental interaction is observed in a single-fin configuration. The planar shock generated by the fin interacts with the boundary layer on an adjacent plate. The flow field generated by single fin configuration is studied in detail by Panaras [1], Settles [2] and others. The crossing shock wave generated by two fins results in a more complex flow separation pattern on the plate. This double-fin configuration is studied experimentally by Zheltovodov et al. [3] and computationally by Gaitonde et al. [4]. Three-dimensional SBLI occurring in inlet ducts can often be characterized in terms of canonical flows. In this paper, the flowfield in a practical intake geometry is studied using computational fluid dynamics. The focus is the impingement and reflection of the cowl shock inside the inlet duct, and the resulting SBLI. A previous study [5] presents a detailed analysis of the three-dimensional shock structure and flow separation in a simplified duct geometry. The current work extends the analysis to a real-life configuration.