The forebody of a hypersonic vehicle based on scramjet propulsion acts as an external compression inlet for the engine. A typical configuration consists of compression ramps and wedges. The flow field generated by these compression surfaces is quite complex. In the absence of experimental data, computational fluid dynamics serves as a valuable tool in understanding the flow physics and predicting the characteristics of the inlet configuration. In this paper, a generic hypersonic forebody geometry consisting of compression ramps and side fences is investigated. The shock and surface flow pattern is examined in detail, followed by the surface pressure and heat transfer prediction on the geometry.