[nmms]

Originally Posted by Archer_CFD

Hello everyone,

I'm new to CFD and need some help modelling an airfoil in Fluent.

I'm modelling both NACA 0012 and NACA 0015 airfoils in 2D. My lift coefficients are very close to experimental values, but drag coefficients are too small (by a factor of about 10).

I am using a C-grid mesh of 40,000 elements and a Reynolds value on the order of 200,000. Currently I am using the viscous-inviscid model and I assume that this is the source of the error.

I have played around with Spalart-Allmaras and k-omega models but I don't know what to do and can not get these to converge.

Any advice on constructing a more accurate simulation would be greatly appreciate.

Thank you.

Hi,

I want to ask some questions to you. I am modeling NACA 0015 now. In my study, aspect ratios are 1.0 and 2.0 but Cl (lift coefficient) profile is not like expected. What was your modelling's aspect ratio? Did you get correct result?

Thank you.