A local correlation-based one-equation transition model was recently proposed for aerodynamics and turbomachinery CFD applications. The model (referred to as 7-model) covers pretty much all modes of transition except the crossflow-induced transition, although it is the dominant mode of transition in flows involving three-dimensional boundary layers such as flow around swept wing, aircraft fuselage, turbine blade, etc. A simple way to account for crossflow effect is proposed, without compromising the simplicity of the original one-equation γ-model formulation. Efforts are also made to include the effect of surface roughness in the crossflow-induced transition. The model is calibrated on a infinite swept wing case where experimental measurements are available. Further tests were performed in test cases involving a sickle wing, prolate spheroid and ONERA-M6 wing to demonstrate the effectiveness of the model. The model is shown to predict reasonably well the crossflow induced transition phenomenon without adding any significant computational overhead.
展开▼
