The local correlation-based transition model was implemented in the unstructured CFD solver U~2NCLE, coupled with the one-equation Spalart-Allmaras (S-A) turbulence model. A zero-pressure gradient flat plate boundary layer flow was used to calibrate the transition model, and several 2D airfoil cases were validated and compared with the experimental data. The skin friction profiles predicted by the transition model indicated that the transition phenomenon was captured reasonably well, including the onset location and the length of transition for a variation of Reynolds numbers and angles of attack. Results of a realistic helicopter rotor showed that the transition model significantly improved the prediction accuracy for lift and drag coefficients when a laminar-turbulent transition is the dominating factor in the flow field.
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