# Wing Lift and drag coefficient

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 April 15, 2012, 07:13 Wing Lift and drag coefficient #1 New Member   Thierry Chavagnan Join Date: Apr 2012 Posts: 6 Rep Power: 5 Hi everyone!!! I am trying to calculate the lift and drag coefficient of a 3D wing in CFX. I know CFX offers viscous force in X, Y and Z direction. My flow is aligned with the the x-axis. Therefore, am I right saying that I can use the force in the x-axis to obtain Cd and the force on the y-axis can be used to obtain Cl ??!! Thank you for your consideration.

April 15, 2012, 17:51
#2
Super Moderator

Glenn Horrocks
Join Date: Mar 2009
Location: Sydney, Australia
Posts: 11,053
Rep Power: 86
Quote:
 I know CFX offers viscous force in X, Y and Z direction.
No, CFX gives the total force in X/Y/Z directions. It does not calculate viscous forces separately. But you may be able to calculate it from integrals of wall shear stress.

Your question is correct. This is the standard definition for Cd and Cl.

 April 16, 2012, 09:26 #3 New Member   Thierry Chavagnan Join Date: Apr 2012 Posts: 6 Rep Power: 5 Thank you so much!! So basically the force in x-axis is also the drag force (skin friction + form drag etc.) and the y-axis is the amount of lift force produced by the wing. From these forces I just have to work out, the Cl and Cd. Thank you once more for your time Kind Regards

 April 17, 2012, 01:18 #4 Super Moderator   Glenn Horrocks Join Date: Mar 2009 Location: Sydney, Australia Posts: 11,053 Rep Power: 86 That's right. force_x/y/z is the total force in that direction.

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