NUMERICAL MODELLING OF A PITCHING AIRFOIL
Keywords:
Airfoil modelling, NACA airfoil, flow field, turbulent model, hysteresis loop.Abstract
The RANS code FluentTM 6.1 is used to predict the flow field around a pitching NACA 0012 airfoil. A hybrid mesh was employed in the computational domain and different mesh configurations are tested and the results are compared. Twoequation turbulence models namely k-є, r k- є, k-ω, and SST k-ω were tested and their results are compared. The turbulence model that gives the best agreement with the experimental data for 2D case is SST k-ω with y+ value set to 1. Mesh and time step dependency checks are also performed and the results show that the cl and cd are not effected by varying the time step and mesh parameters. However it was observed that time step and mesh independent predictions for the cm hysteresis loop could not be obtained.References
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