Discussion
A section has profile drag coefficient \(c_d = 0.008\) and lift coefficient \(c_l = 0.8\). Its section lift-to-drag ratio is
Answer: B
Correct answer: 100
\[ \frac{l}{d} = \frac{c_l}{c_d} = \frac{0.8}{0.008} = 100. \] Section lift-to-drag ratios of this order are ordinary, because a two-dimensional section has no induced drag. A complete aircraft does far worse - fifteen to twenty for a transport - and almost all of the difference is induced drag and the drag of everything that is not the wing.
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