Question: A rectangular, untwisted wing of aspect ratio 3 has an airfoil section for which the lift-curve slope is 6 in two-dimensional flow. Take the distribution of circulation across the span of a wing to be given by
Γ = 2sUΣAnsin nΘ
and use the general theory for wings of high aspect ratio to determine the approximate circulation distribution in terms of angle of attack by retaining only two terms in the expression for circulation and satisfying the equation at θ = π/4 and π/2.