There is a rectangular wing with aspect ratio of 3.5, its profile is NACA0006 airfoil, and

Question:

There is a rectangular wing with aspect ratio λ of 3.5, its profile is NACA0006 airfoil, and it flies in a steady straight line at Ma∞ = 0.85 at the altitude of 12 km. Try to calculate the relative thickness t of the airfoil corresponding to the affine-related wing in incompressible flow after an affine transformation and aspect ratio λ。