The aircraft in problem 1 has a CD,o of 0.027, and an Oswald's efficiency of 0.8. a. What is the value of K for this aircraft? (1 pt) b. Plot a drag polar for this airplane from a C of 0 to 1.5. (3 pt) c. Plot the L/D over the same range of lift coefficients. (3 pt) d. Assuming a section lift curve slope of 2 1/rad, what is the vehicle lift curve slope based on the aspect ratio from 1a? (1 pt) e. If the wing generates a C of 0.2 at zero angle-of-attack and has a max lift coefficient of f. 1.5, plot the CL vs angle-of-attack, assuming a linear trend. (3 pt) What is the cruise drag coefficient for this vehicle? (1 pt) g. What is the cruise angle of attack? (1 pt) h. What is the approach/landing drag coefficient? (1 pt) i. What is the approach/landing angle of attack? (1 pt)