Computational fluid dynamics (CFD) has become a powerful ally of the experimental test facility in revealing the flow physics of some highly complex flows. For certain classes of flow, CFD has reached maturity and is therefore being increasingly used in industry by designers. This paper is intended to show current transonic prediction capability at GE Aircraft Engines in terms of a recently developed three-dimensional Navier–Stokes code. The flow simulations addressed are concerned with transonic fan design and illustrate those issues that are important to designers such as tip leakage flow, shock boundary layer interaction, boundary layer growth, and account of internal solid bodies such as part-span shrouds and engine splitters. In this respect, three successively more complex Navier–Stokes simulations representative of modern fans—NASA Rotor 67, GE/Wennerstrom Rotor 4, and the GE/NASA E3 fans—are considered in this paper.

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