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NACA 0012 Airfoil CFD Analysis (H.B) - Copy

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v1rtu4l702
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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

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Project History

  • HamzaBaig

    HamzaBaig created this project

  • v1rtu4l702

    v1rtu4l702 copied this project