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An aircraft with elliptic wing planform has parasite drag coefficient as 0.9. Lift coefficient of wing is 1.8 and aspect ratio is 8.5. Find total drag coefficient for the wing.

Correct Answer: 1.021
Given, elliptic wing, parasite drag coefficient CD0 = 0.9 Lift coefficient CL = 1.8, Aspect ratio AR=8.5 Now, Total drag coefficient = Parasitic drag coefficient (CD0) + induced drag coefficient (CDi) CDi = CL*CL / (ᴨ*e*AR) = 1.8*1.8 / (ᴨ*1*8.5) = 0.121 Hence, Total drag coefficient = CD0 + CDi = 0.9 + 0.121 = 1.021.

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