Abstract
Numerical simulation of flow past airfoils in the stalled region is a difficult problem due to some phenomena like strong vortex dynamics, boundary layer separation due to adverse pressure gradient etc. For accurate numerical prediction of separated flow, correct modelling of boundary layer is very much necessary to capture the details of the fluid flow. The following work is the CFD analysis of NACA 23024 airfoil. The analysis is carried out for a free stream Reynolds number of 6 million for which the wind tunnel results are available. The CFD analysis is carried out using Ansys Fluent Solver. The analysis is carried out using K-Epsilon turbulence model, Lift and drag coefficients measured in wind tunnel are compared with the CFD analysis results and the performance of the turbulence model is discussed
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