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