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3D Airfoil Cl and Cd validation issues ?

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Old   January 19, 2019, 12:06
Exclamation 3D Airfoil Cl and Cd validation issues ?
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Aamir Sultan
Join Date: May 2018
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Hello Everyone ,

I am working on a 3D airfoil for quite a bit of time . I am comparing the results obtained from wind tunnel with that of CFD simulation .

Although , the results of my 2D simulations are quite match-able with the 2D version of wind tunnel data .

However , for 3D the results (values of Cl and Cd) I am obtaining from CFD simulations are 25-30 % lower than that of wind tunnel data .

) I have taken care of the first cell height while generating mesh.I have taken the vale of Y+ =1 , and calculated the first cell height.

2) I am using Spalart Allmaras Turbulence Model ( 2D simulations gave good results for this model , so I am using it for 3D simulation )

3) At low angle of attacks I am running steady state analysis , at higher angle of attacks > 10 degrees I change it to transient time averaged .

PS: I had cross checked the reference values too. But nothing seems to work .
I can share case file with you , if you could have a look on it , as I am trying to resolve this issue for more than 3 months but I am unable to get the desired results.
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drag and lift, drag coefficient, lift coefficient, validation

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