The machine that is the subject of this work has been used for numerous experimental studies over a number of years. It is representative of the aft stages of a core compressor in which the flow is entirely subsonic. The experimental studies have been primarily focused on vane clocking and the related effects on compressor performance, as well as stall margin; a multi-year study was recently completed, which looked at tip-clearance effects. This paper is, on the other hand, an entirely computational effort that will make use of the extensive experimental database associated with this machine in order to validate the numerical results. The plan will then be to conduct further fundamental aerodynamic research in a collaborative experimental/computational setting. The results are encouraging, but they should be taken as preliminary in their context.