✈️ ANSYS Fluent Tutorial | Lift and Drag Coefficient Calculation for NACA Airfoil
✈️ ANSYS Fluent Tutorial | Lift and Drag Coefficient Calculation for NACA Airfoil
In this ANSYS Fluent tutorial, we’ll perform a 2D CFD simulation of a NACA 0012 airfoil to calculate lift and drag coefficients with high accuracy. You’ll learn how to create the geometry in *SpaceClaim*, generate a refined mesh, and set up the boundary conditions, solver parameters, and turbulence model (k-ω SST).
We’ll also visualize important results such as:
Velocity contours around the airfoil
Y-Plus distribution for mesh quality assessment
Lift and drag coefficient plots for aerodynamic performance evaluation
By the end of this video, you’ll understand how to ensure accurate results for aerodynamic analysis using ANSYS Fluent.
📌 What You’ll Learn:
✅ How to model a NACA 0012 airfoil in ANSYS SpaceClaim
✅ How to refine mesh zones for accurate Y+ control
✅ How to set up and run steady-state simulations in Fluent
✅ How to compute lift (CL) and drag (CD) coefficients
✅ How to analyze flow visualization results
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0:00 3:17 Introduction
3:18 5:53 Airfoil text file
5:54 15:51 Geometry preparation
15:52 19:33 Initial mesh
19:34 21:52 Viscous model & material
21:53 23:42 Boundary conditions
23:43 26:01 Method and FMG initialization
26:02 27:41 Results and Yplus
27:42 29:00 Modified mesh
29:01 29:57 Recheck the model
29:58 31:29 Lift & drag report reference values
31:30 33:38 Results & comparison
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