In continuing the effort to push the limitations of modern gas turbine engines, Ultra Compact Combustors offer unique solutions to minimize engine size and weight. They accomplish this by reducing the number of components in the engine core and perform the combustion in a circumferential cavity that encircles the core flow. Within this cavity, the fuel is injected rich. Burning continues to occur ... [Show full abstract] in the vane passage beneath the circumferential cavity which must be completed in a controlled manner prior to the inlet plane of the rotor. Furthermore, the temperature distribution at the exit of the vane passage must be controlled to generate high work extraction from the turbine. This research shall vary the cavity equivalence ratio, g-loading, swirl direction, and mass flow ratio with the core flow to characterize the impact of each of these parameters on the exit conditions. The primary metrics for comparison are the exit temperature and pressure profiles, the emissions characteristics, and the overall Rayleigh losses. The goal of this particular investigation was to establish a set of criterion that produced an exit flow condition similar to that created by a traditional axial combustion system, thus realizing the weight savings offered by the ultra compact design. Results will show that the shape of the exit temperature profiles are independent of cavity equivalence ratio and more sensitive to the distribution of mass flow.