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Air stream flows horizontally past an aeroplane wing of surface area 4 m². The speed of air over the top surface is 60 ms^-1 and under the bottom surface is 40 ms^-1. The force of lift on the wing is (Take, density of air = 1 kgm^-3)

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800 N

1000 N

4000 N

3200 N

answer is B.

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Detailed Solution

Pressure difference, $Δ p = Δ K E = \frac{1}{2} \times p (v_{1}^{2} - v_{2}^{2})$

or $Δ p = \frac{1}{2} \times 1.0 \times (3600 - 1600) = 1000 {Nm}^{- 2}$

$\Rightarrow F = (Δ p) \times A = 4000 N$

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