NACA0012 Airfoil Validation with the Compressible Flow, CFD Simulation ANSYS Fluent
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.
This product includes Geometry & Mesh file and a comprehensive Training Movie.
There are some free products to check our service quality.
To order your ANSYS Fluent project (CFD simulation and training), contact our experts via [email protected], online support, or WhatsApp.
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.
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 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:
|Spalart Allmaras Production||Strain/Vorticity-based|
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|
|Flow & Modified turbulent viscosity||Second-order upwind|
|gradient||Green Gauss Node-based|
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|