NACA 0012 Airfoil CFD Analysis (H.B)

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HamzaBaig
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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.

airflowairfoilcfddragincompressible flowliftpressure dropvelocitycfd modelinglearning

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  • HamzaBaig

    HamzaBaig created this project

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