Goto has presented data in the literature for the Deverson axial flow compressor rotor in a single stage environment. The flow features tip leakage and hub corner stall. In this paper, 3-d turbulent steady flow calculations for the rotor are used to determine if, and how, this rotor can be a useful CFD test case. The sensitivity of the CFD results to unknowns about the test case environment is computed. In particular the influences of blade twist, hub gap leakage flow between rotating and stationary components, and a departure from a radial equilibrium pressure distribution at the rotor exit are investigated. Evidence in support of these phenomena is presented and discussed, their likely magnitudes are suggested, and their influence on the rotor performance is quantified.

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