NACA0012 Airfoil, Compressible Flow, Paper Validation

Description

NACA0012 Airfoil (Compressible Flow), Paper Numerical Validation, ANSYS Fluent CFD Simulation training

In this project, We simulated the compressible flow around the NACA0012 airfoil by Ansys Fluent Software. Then we compared the results with the results extracted from an article called this “Numerical Simulation OF VISCOUS TRANSONIC AIRFOIL FLOWS”.

Geometry & Mesh

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:

Models
Viscous		Spalart Allmaras
	Spalart Allmaras Production	Strain/Vorticity-based
Boundary conditions
Fairfield		Mach Number
	Pressure Fairfield	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
Methods
Formulation Flux type		Implicit Roe-FDS
	Flow & Modified turbulent viscosity	Second-order upwind
	gradient	Green Gauss Node-based
Initialization
Initialization methods		Standard
	Compute from	Far-field
Material
Material properties
	density	Ideal gas
	viscosity	Sutherland
	Cp	1006.43

Paper Validation Results

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

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