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NACA 0012 Airfoil CFD Analysis
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Statistics
1 Geometry
2 Meshes
1 Simulation setup
0 Results
1 Geometry 2 Meshes 1 Simulation setup 0 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
