Boundary layer effects, tip clearance flow details, and wake unsteadiness in blade passages are modeled efficiently using Fluent's flexible mesh topologies and interactive controls for mesh distribution. Fluent provides mesh embedding, nonconformal interfaces, and hybrid meshes to help you resolve small flow details. Fluent also provides a coupled solution method designed to deliver robust convergence performance for transonic flows. Built-in parallel processing dramatically reduces the turnaround time on computations.

NASA Rotor 67 axial flow fan -- Mach number distribution on the hub and blade surfaces