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

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Old   May 18, 2011, 22:39
Default Reference Area for Calculating Lift and Drag Coefficient of 3D wing
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Mahbub Islam
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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.
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Old   May 19, 2011, 00:03
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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.
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Old   May 19, 2011, 00:10
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Praveen

Thank you so much. Now I have got the point.
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Old   May 19, 2011, 00:21
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Quote:
Originally Posted by mahbub03 View Post
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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