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NACA 0012 Airfoil CFD Analysis (H.B) - Copy
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5Â Geometries
3Â Meshes
2Â Simulation setups
2Â Results
5Â Geometries 3Â Meshes 2Â Simulation setups 2Â ResultsAbout this project
In this project we examined the Effect of Boundary Layers on the NACA 0012 Airfoil. In-compressible fluid flow simulation is selected for the project. Free stream velocity is selected as 10 m/s having A.O.A 10 with the airfoil. - Copy
