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Bernoulli's Principle

Air stream ho...

Question

Air stream horizontally across an aeroplane wing of area 3m $^{2}$ weighing 250 kg. The air speed is 60 m/s and 45 m/s over respectively. What is the lift on the wing ? (Density of air 1.293 g/1)

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Solution

$Δ P = \frac{1}{2} ρ (v_{2}^{2} - v_{1}^{2})$

Lift $= L = Δ P A = \frac{1}{2} ρ (v_{2}^{2} - v_{1}^{2}) A$

$⟹ L = \frac{1}{2} \times 1.293 \times (60^{2} - 45^{2}) \times 3$

$⟹ L = 3054.7 N$

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