(b) Consider a finite wing with an aspect ratio of 7, the airfoil section of the wing is a symmetrical airfoil with an infinite wing lift slope of 0.11 per degree. The lift-to-drag ratio of this wing is 29 when the lift coefficient is equal to 0.35. In a later modification, the angle of attack remains the same and the aspect ratio is simply increased to 10 by adding an extension to the wing. Assume that the span efficient factor is 0.9 for both cases. Apply the finite wing theory to compute the original finite wing lift slope. (ii) Appraise the wing geometry AOA. C (111) Analyse the new Lift-to-Drag ratio.