3D Wing Analysis
 

Hello Everyone!

I am analyzing a 3D wing for my project.
The Coefficient of Lift Values are not matching with the wind tunnel values.
Can somebody please help me out on this?!

Cl of wind tunnel = 0.88
Cl of Star CCM + = 0.45
I am using a velocity inlet and a pressure outlet. Inlet velocity is 11.7 m/s.

The airfoil is FX 63137.
Chord = 220mm
Span = 1200mm

The Physics Conditions are:
Steady, Gas, Constant Density, Segregated Flow, K-Epsilon Turbulence.
I have used a prism layer Mesher.

Thank you:)

probably a mesh issue. hard to say without more info.