Consider a rectangular wing with an aspect ratio of 6, an induced drag coefficient = 0.055,

Consider a rectangular wing with an aspect ratio of 6, an induced drag coefficient δ = 0.055, and a zero-lift angle of attack of −2°. When the angle of attack is 3.4°, the induced drag coefficient of the wing is 0.01. Calculate the induced drag coefficient of a similar wing (a rectangular wing with the same airfoil profile) with the same angle of attack and an aspect ratio of 10. Assume that the inducing factors δ and τ of drag and lift slope are, respectively, equal (i.e., δ = τ ). Similarly, for λ = 10, δ = 0.105.