Aerospace Engineering > GATE 2010 > Lifting Line Theory
Consider a potential flow over a finite wing with the following circulation distribution
Γ(y)=100√1-(2y/4)2m2/s
If the free stream velocity is 100 m/s, the induced angle of attack is
Γ(y)=100√1-(2y/4)2m2/s
Correct : b
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