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mahbub03 May 18, 2011 22:39
Reference Area for Calculating Lift and Drag Coefficient of 3D wing
 
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.

praveen May 19, 2011 00:03
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.

mahbub03 May 19, 2011 00:10
Praveen

Thank you so much. Now I have got the point.

cfd_newbie May 19, 2011 00:21
Quote:
Originally Posted by mahbub03 (Post 308251)
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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