Just need help with problem 3. Must be solved in Given, Find, Solution format.

w Problem 3 (25 points). The Cessna Cardinal, a single-engine light plane, has a wing with an area of 16.2 m and an aspect ratio of 7.31. Assume that the span efficiency factor is 0.62. If the airplane is flying at standard sea-level conditions with a velocity of 251 km/h, what is the induced drag when the total weight is 9800 N? Problem 4 (25 points). Consider a finite wing with an aspect ratio of 7; the airfoil section of the wing is a symmetric 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. 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-to-drag ratio? Assume that the span efficiency factors e-e-0.9 for both cases. View Rubric