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How to find Line Cp at different wing spans-0.44, 0.80, 0.95 in fluent?

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November 11, 2017, 15:49	How to find Line Cp at different wing spans-0.44, 0.80, 0.95 in fluent?	#1
FluidAerodynamics New Member California Join Date: Nov 2017 Posts: 2 Rep Power: 0	Hello, I am trying to find Cp at different spans of a 3d wing airfoil- 0.2, 0.44, 0.8, 0.95. I do not how to find the both x-points of the chord. Please help ASAP. I could do the 0.2 Cp because both the x points at the chord ends were known, But I don't know the same for the different spans. Please let me know asap.!

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airfoil., coefficient of pressure, fluent, wing, wing chord

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