ANSYS Fluent Tutorial | NACA 0012 Airfoil at Re = 50,000 | CFD vs Experimental Data

In this ANSYS Fluent tutorial, we simulate external flow around a NACA 0012 airfoil at a Reynolds number of 50,000 and compare the CFD results with published experimental data. The tutorial covers the complete CFD workflow, including geometry setup, computational domain, boundary conditions, meshing, solver setup, force coefficient reports, and post-processing of lift and drag coefficients. For this case, the CFD result gives: CL = -4.9e-05 CD = 0.0251 The published/experimental result is approximately: CL ≈ 0 CD = 0.026 The CFD-predicted lift coefficient is very close to zero, which is expected for a symmetric NACA 0012 airfoil under the simulated condition. The predicted drag coefficient also shows good agreement with the published value. This tutorial is suitable for beginners who want to learn how to set up an airfoil CFD simulation in ANSYS Fluent and compare lift and drag coefficients with experimental data. What you will learn: How to set up a NACA 0012 airfoil case in ANSYS Fluent How to define external flow boundary conditions How to calculate lift and drag coefficients How to compare CFD results with experimental data How to interpret CL and CD results for an airfoil simulation #ANSYSFluent #CFDTutorial #NACA0012 #NACA0012Airfoil #AirfoilCFD #CFDForBeginners #ExternalFlowSimulation #ReynoldsNumber50000 #LiftCoefficient #DragCoefficient #CFDValidation #CFDComparison #ExperimentalData #FluentTutorial #ComputationalFluidDynamics #Aerodynamics #AirfoilSimulation #SteadyRANS