# Reference Area for Calculating Lift and Drag Coefficient of 3D wing

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 May 18, 2011, 22:39 Reference Area for Calculating Lift and Drag Coefficient of 3D wing #1 New Member   Mahbub Islam Join Date: Mar 2010 Location: Bangladesh Posts: 25 Rep Power: 9 Sponsored Links Hi Everyone, I am having a confusion on calculating reference area for 3D wing. As I know, for the Lift coefficient the reference area is SPAN*CHORD of the wing. But for calculating Cd should that also be SPAN*CHORD? or the frontal area perpendicular to the flow direction? Thank you for your time. It would be a great help if anybody gives this info.

 May 19, 2011, 00:03 #2 Super Moderator     Praveen. C Join Date: Mar 2009 Location: Bangalore Posts: 259 Blog Entries: 6 Rep Power: 11 It has to be some area. Which one to use will depend on the data you are going to compare it with. Which area was used to define that data ? If you have nothing to compare, you can use span*chord. If its not a straight wing, use the planform area. Its same for both cl and cd.

 May 19, 2011, 00:10 #3 New Member   Mahbub Islam Join Date: Mar 2010 Location: Bangladesh Posts: 25 Rep Power: 9 Praveen Thank you so much. Now I have got the point.

May 19, 2011, 00:21
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Raashid Baig
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Quote:
 Originally Posted by mahbub03 Hi Everyone, I am having a confusion on calculating reference area for 3D wing. As I know, for the Lift coefficient the reference area is SPAN*CHORD of the wing. But for calculating Cd should that also be SPAN*CHORD? or the frontal area perpendicular to the flow direction? Thank you for your time. It would be a great help if anybody gives this info.
It's SPAN*CHORD for Cd too.

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