naca 12 error
 

Hi I'm trying to preform a simple calibration test on CFX10 to run a range of angles of attack for a NACA 12 foil at a Reynolds number of 600,000 and compare my results with official NACA data.

I've set my NACA foil up very similar to the boundary conditions and other settings used in the tutorial WingSPS only changing the setting supersonic to subsonic and obviously reducing my velocity to about 92m/s. I'm also using tetra mesh with a fine layer of prisim mesh around the foil.

I've tried a million different mesh desities and tried many different turbulent intensity values and turbulent length scale values with very little difference between each in my results. My Y+ value is well under 1 all over the entire foil. For an angle of 8 degrees my error is still a massive 10 percent for lift and off the chart for drag. I think I'm doing something seriously wrong. I would really appreciate any help you might be able to previde????

Conor