First slide

Fluid dynamics

Question

Air streams horizontally across an aeroplane wing of area $3 m^{2}$ weighing $250 k g$ . The air speed is $60 m / s$ and $45 m / s$ over the top surface and under the bottom surface respectively. What is the lift on the wing? (Density of air $1.293 g / l$ )

Moderate

A

$3000 N$
B

$3500 N$
C

$4000 N$
D

$3054 N$

Solution

Lift on the wing $= \frac{p}{2} A (v_{1}^{2} - v_{2}^{2})$ $= \frac{1.293}{2} \times 3 [{(60)}^{2} - {(45)}^{2}]$
$= 0.6465 \times 3 \times 105 \times 15$ $= 3054 N$

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