[JoshLaz]

Hello,

So I'm a very new user, I'm trying to self teach so please excuse my ignorance if I'm making particularly dumb/un-informed statements.

I've run Ansys Fluent for a wing, I used the symmetry axis setting (thus the forces will be for half the wing, correct?) in the enclosure tool, my problem is that the lift and drag coefficients don't seem to match up with my manually computed coefficients nor rough estimates from OpenVSP's VSPAERO results...

I have a NACA 2313 rectangular wing with chord of 6.67" and half span of 47". When I divide the forces (outputted by fluent) by the dynamic pressure and the half area (chord * half span (converted to m^2)) I get coefficients of lift that match the expected results from VSPAERO (image of those results attached). However the values for the coefficient of lift outputted by fluent directly seem completely arbitrary, when I multiply them by the area and dynamic pressure they don't even give me the forces that fluent itself output...

I've attached an excel file with my results in it, you'll see the output CL under the column labeled "CL" and the calculated CL under "CL Calc".

Any help would be much appreciated, again my apologies if this is a dumb question.