An airfoil is given by a parabolic camber line, i.e., (z_{a}=-left(a / b^{2} ight) x^{2}). Find: (i)

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An airfoil is given by a parabolic camber line, i.e., \(z_{a}=-\left(a / b^{2}\right) x^{2}\). Find: 

(i) sectional lift coefficient, 

(ii) center of pressure, 

(iii) aerodynamic center, at zero angle of attack.

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