Drag coefficient error

jsuf · July 12, 2011, 02:01

Hi all,

I'm relatively new to CFD and could use a few pointers on my following problem.

I'm using Gambit 2.4.6 to generate a NACA0006 airfoil then Fluent 13 to calculate lift and drag coefficients at several angles of attack. Reynolds number is 3e6, laminar model, pressure based solver.

I have refined the mesh several times and have converged on a lift and drag value for each case. Comparing to Xfoil and 'Theory of Wing Sections' my lift is in the order of 2-7% accurate but for almost every case my drag is approximately double.

I've tried to refine the mesh further close to the airfoil surface but after a certain level of refinement my continuity residual no longer converges.

Thoughts?

Regards,
Josh

Rhyno466 · July 13, 2011, 16:12

What turbulence model are you using?

July 12, 2011, 02:01	Drag coefficient error	#1
jsuf New Member Josh Join Date: Jul 2011 Posts: 3 Rep Power: 14	Hi all, I'm relatively new to CFD and could use a few pointers on my following problem. I'm using Gambit 2.4.6 to generate a NACA0006 airfoil then Fluent 13 to calculate lift and drag coefficients at several angles of attack. Reynolds number is 3e6, laminar model, pressure based solver. I have refined the mesh several times and have converged on a lift and drag value for each case. Comparing to Xfoil and 'Theory of Wing Sections' my lift is in the order of 2-7% accurate but for almost every case my drag is approximately double. I've tried to refine the mesh further close to the airfoil surface but after a certain level of refinement my continuity residual no longer converges. Thoughts? Regards, Josh

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July 13, 2011, 16:12		#2
Rhyno466 Member Ryne Join Date: Jan 2010 Posts: 32 Rep Power: 16	What turbulence model are you using?