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NACA 0012 Airfoil CFD Analysis - Copy
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Statistics
1 Geometry
3 Meshes
2 Simulation setups
2 Results
1 Geometry 3 Meshes 2 Simulation setups 2 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 - Copy
