For such a wing with varying chord, the mean aerodynamic chord (MAC) is defined as \mathrm{MAC}=\frac{2}{5} \int_{0}^{b / 2} c^{2} d y where y is the coordinate along the wing span and c is the chord at the coordinate y. Knowing tipchord length (C₂), root chord length (Cr), and the span (b) of a linearly tapered wing, show thatMAC will become: M A C=\frac{2}{3} c_{T}\left(\frac{1+\lambda+\lambda^{2}}{1+\lambda}\right) where λ=c/cr.Hint: You can start from a linearly tapered wing described below.