NACA0012 Airfoil Validation with the Compressible Flow, CFD Simulation ANSYS Fluent

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In this project, we intend to simulate the NACA0012 airfoil with the compressible flow around it to compare and validate the results with the results in the article.

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NACA0012 Airfoil Project Description

In this project, We simulated the compressible flow around the NACA0012 airfoil by Ansys Fluent Software, and then we compare the results with the results extracted from an article called this “numerical SfMULATfON OF VISCOUS TRANSONIC AIRFOIL FLOWS”.


The geometry is designed by the design modeler Software.

NACA0012 AirfoilNACA0012 Airfoil

The meshing of this present model has been generated by ANSYS Meshing software. The mesh grid is structured, and the total cell number is 73320.

NACA0012 AirfoilNACA0012 Airfoil

NACA0012 Airfoil CFD Simulation

To simulate the present model, several assumptions are considered, which are:

  • The solver is density-based due to compressibility.
  • Simulation has been done as steady State
  • We ignored the gravity effect.

The following is a summary of the steps for defining the problem and its solution:

Viscous Spalart Allmaras
Spalart Allmaras Production Strain/Vorticity-based
Boundary conditions
Farfield Mach Number
Pressure Farfield 0.7

X-component of flow direction: 0.9996435

Y-component of flow direction: 0.02670036

Airfoil Up & Airfoil Bottom Wall
Wall motion Stationary Wall
Shear Condition No-slip condition

Flux type



Flow & Modified turbulent viscosity Second-order upwind
gradient Green Gauss Node-based
Initialization methods Standard
Compute from Far-field
Material properties
density Ideal gas
viscosity Sutherland
Cp 1006.43


By comparing the simulation results with the results in the article, it can be concluded that the simulation has been validated with the article.

Coef. Experimental Value CFD Value
CD 0.0079 0.00804
CL 0.241 0.246



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