The overall drag coefficient of an aircraft of weight W and wing area S is given by $C_{D} = a + b {C_{L}}^{2}$ where a and b are constants. The maximum drag in horizontal flight will be

- 1
  
  $W \sqrt{a b}$
- 2
  
  $2 W \sqrt{a b}$
- 3
  
  $4 W \sqrt{a b}$
- 4
  
  $6 W \sqrt{a b}$

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