Aerospace Engineering > GATE 2019 > Lift Calculation
The span-wise distribution of circulation over a finite wing of span b = 10 m is
. If Γ0 = 20 m2/s and the free stream density and speed are 1.2 kg/m3 and 100 m/s, respectively, the total lift is _______ kN (round off to 2 decimal places).
Correct : 18.00 to 19.20
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