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?