|March 14, 2016, 10:39||
3D Wing Analysis
Join Date: Mar 2016
Posts: 1Rep Power: 0
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.
|coefficient of lift, wing|
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