[cfdseeker]

I have no good experience to aerodynamic analysis. I did some assignments in University days but I want to laern more and doing the validation as per given from here http://turbmodels.larc.nasa.gov/naca0012_val.html.

However I first run at angle of 10 deg but I get very small Cl. I think I am doing some mistake in setup or calculation.

Few questions...
I read in books that in 2D, the lift coefficient Cl is per unit span length, so the equation for coefficient of lift is:

cl_2D=Lift per span length/(0.5 * rho * V^2 * C)

In 3D it is

CL_3D=Lift/(0.5 * rho * V^2 * A)

C is chord length, and rho and V are the freestream conditions and A is planform area..

Now, if I do 2D simulation in fluent, How do I calculate cl_2D coefficient in 2D manually using above formula? Is this Cl calculation would tally with the NASA validation data?

Sorry for my poor English, its not my first language

[oj.bulmer]

Lift/span in 3D should be equal to Lift produced in 2D simulation in FLUENT and the Cl data should match with results