The drag of an airfoil at zero angle of attack is a function of density, viscosity, and velocity, in addition to a length parameter
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2
+ 1 = 0
2
= -1 ;
-
2
- 1 = 0
2
= -1; -3(-1) + (-1) +
2
- 1 = 0
2
= -1
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2 + 1 = 0 2 = -1 ;