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4. An experimental aircraft has a wing area of = 54 m', a wingspan of b = 18 m, and a weight of W = 12225 kg. The aircraft is flying at an altitude of hc = 7.6 km and a velocity of Vi. = 414 km/hr. Experimental data gives us a span efficiency factor of e = 0.88 and a polar drag coefficient of cg ~ 0.0066. Using this information, along with details from Example 5.25 - 5.29, and the appropriate appendices, make the following calculations. Points are noted next to each Part. a. Calculate the dynamic pressure (g~) under these conditions in N/m?. (2 Points) b. Calculate the coefficient of lift (Cz). (2 Points) c. Calculate the induced drag coefficient (Cp,i). (3 Points) d. Calculate the induced drag (Dj) in Newtons (AN). (3 Points) e. Calculate the total drag coefficient (Cp). (2 Points) f. Calculate the total drag (D) in Newtons (A). (2 Points)