NACA 0008 Drag Results - Help Required
 

Hi everyone. I seem to have run into a bit of a problem with one of my CFD simulations in ANSYS Fluent 18.1: a NACA 0008 aerofoil (chord length = 50mm) at 0º AoA and speeds of 35 m/s in order to get some lift and drag results to compare to the actual experiment that took place in a wind tunnel. The problem is that the drag results I am getting so far are off by a factor of 10 and I am really not sure what to do now. I would appreciate any help/suggestions at all as I have run out of my own ideas.

Here are the details of the set up:

Fluid: air
Reynolds Nmbr: approx. 100000
Expected Drag Coefficient: 0.015
Drag result produced by Fluent: approx. 0.001
Number of nodes: 370k

Here is a link to some screenshots with extra details:https://imgur.com/p3hvFO1
Again, I appreciate any suggestions!