(d) Compute the total lift generated by the combination wing plus flap system by integrating the lift at a given section, L'(y), over the wing span, i.e., b/2 L = L + L = pV Tw(y)dy + pV fold Fr(y)dy. -6/4 To solve these integrals use the same transformation suggested in point (a). The lift can also be expressed as L = PVSCL, where S is the area of the wing planform and CL is the lift coefficient of the wing. Using the results above, compute the area of the flap system, S,, necessary to increase the lift of the wing alone L by 20%.