- #1
maomao39
- 12
- 0
I am running ANSYS fluent simulation flow over naca 0012 airfoil.
So far the lift coefficient is similar with the published papers.
The problem is drag coefficient is different so much in term of value compared to published papers.
I have check my mesh quality and boundary condition, it shows no problem.
Any idea why drag coefficient is different ?
So far the lift coefficient is similar with the published papers.
The problem is drag coefficient is different so much in term of value compared to published papers.
I have check my mesh quality and boundary condition, it shows no problem.
Any idea why drag coefficient is different ?