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

mahbub03 · May 18, 2011, 22:39

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

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.

May 18, 2011, 22:39	Reference Area for Calculating Lift and Drag Coefficient of 3D wing	#1
mahbub03 New Member Mahbub Islam Join Date: Mar 2010 Location: Bangladesh Posts: 24 Rep Power: 16	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 SPANCHORD of the wing. But for calculating Cd should that also be SPANCHORD? 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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May 19, 2011, 00:03		#2
praveen Super Moderator Praveen. C Join Date: Mar 2009 Location: Bangalore Posts: 342 Blog Entries: 6 Rep Power: 18	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
mahbub03 New Member Mahbub Islam Join Date: Mar 2010 Location: Bangladesh Posts: 24 Rep Power: 16	Praveen Thank you so much. Now I have got the point.