[badwalgurpreet]

Hello, Dear OpenFOAM Users,

I am trying to validate NACA 0012 airfoil simulation using OpenFOAM 5.0x using simpleFoam solver. I created a C-H type mesh using Pointwise meshing tool and successfully exported to OpenFOAM. My simulations inputs are as follow:

(1): Free Stream Velocity = 45 m/s
(2): Mach Number = 0.13
(3): Free Stream Pressure ( (101325 pa) and Temperature (300 k )
(4): Density of air = 1.225
(5): Kinematic Viscosity = 1.4607*10^-5
(6): Reynolds Number = 3.0807 *10^6

I run this case for Angle of Attack (A.O.A) = 10 degrees and I got the results for Lift and Drag Coefficients like
Cd = -0.00339582
Cl = 0.0797399

which seems incorrect.


Can someone help me how to get the right values of Cl and Cd ?


0.tar.gz

system.tar.gz

checkMesh.pdf

constant.tar.gz

0.tar.gz

system.tar.gz

checkMesh.pdf

constant.tar.gz

residulas.png