Consider a finite wing with an aspect ratio of 7; the airfoil section of the wing is a symmetric airfoil with an infinite-span lift slope of 0.11 per degree. The lift-drag ratio for this wing is 29 when the lift coefficient is equal to 0.35. If the angle of attack remains the same and the aspect ratio is simply increased to 10 by adding extensions to the span of the wing, what is the new value of the lift-drag ratio? Assume that the span efficiency factors e = 0.9 for both cases.