Lift and Pressure Question ( )

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To determine the coefficient of lift (Cl) using the average coefficient of pressure (Cp) on the upper surface of a wing, it's essential to recognize that this surface contributes 3/4 of the total lift. The relationship between Cp and Cl can be established through the integration of Cp over the wing's surface. To solve the integrand for the Cl integral, one must integrate the Cp values across the relevant area of the wing, factoring in the freestream velocity (V). The final Cl can be calculated by applying the appropriate aerodynamic formulas to the integrated results. This approach will yield the coefficient of lift based on the given parameters.
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I also posted this in the homework help, but I may get more help here.

This is the problem:

We are given either a local velocity or local coefficient of pressure. Using one, the other can be solved. Freestream V is given.

Now, if that Cp is the average Cp on the upper surface of a wing and that upper surface provides 3/4 of the lift, what is the coefficient of lift?

How would I solve the integrand of the cl integral?
 
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