# Are there any reference values for Cl and Cd of a NACA 0012 airfoil to verify CFD simulations?

I am having trouble finding the established results of inviscid flow CL and Cd variation over NACA 0012 airfoil, for the transonic region. I need the data to verify the results I am getting through my CFD simulations. I have recently started learning CFD and the actual results would be really useful to me as they would clarify whether I am in the right direction or not.

Please suggest any site, research paper or book.

• Did you try scholar.google.com? The first hit when searching for 'NACA 0012 transonic' delivers some windtunnel results Jul 28, 2016 at 13:51
• The inviscid c$_D$ of a NACA 0012 is the same as for all other airfoils: 0! Jun 26, 2017 at 20:08

$C_L$ and $C_M$ are more extensively represented in the reference books than $C_D$, which is more generally lumped into considerations of Mach divergence number. The same two books will help you further.