How Do You Calculate the Coefficient of Lift from Local Cp and Velocity?

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To calculate the coefficient of lift (Cl) from local coefficient of pressure (Cp) and velocity, one can use the relationship between Cp and Cl, given that the freestream velocity (V) is known. If the average Cp on the upper surface of a wing accounts for 75% of the lift, the Cl can be derived by integrating Cp over the wing's surface from leading edge (LE) to trailing edge (TE). The formula for Cl is expressed as Cl = ∫(Cp) dx. Understanding the integrand and the limits of integration is crucial for solving the problem accurately. This method provides a systematic approach to determining lift based on local pressure distributions.
physicsCU
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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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I'm not sure I follow the problem as stated, but

from your textbook (I'm sure)

c_l=\int_{LE}^{TE}c_p dx
 

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