[jganiele]

Hi all,

I am simulating different airfoil using Flow Simulation, and I cannot obtain values ​​of the lift and drag coefficients consistent with the bibliography.

I was reading several topics, and found that they talked about the importance of the reference system to obtain the correct values, but I do not quite understand how this works. If someone has experience in the subject, it would help me a lot.

Wizard:
- External flow
- Fluid: Air
- Density: 1.225 kg/m3
- velocity in x: 12 m/s
- attack angel: 0º
- airfoil: Naca 4412
- chord leght: 0.145 m