First slide

Fluid dynamics

Question

Air streams horizontally across an aero plane wing area $5 m^{2}$ weighing 300 kg. The air speed is 30 m/s and 20 m/s over the top surface and the bottom surface respectively what is the lift on the wing? (density of air 2grm/ litre)

Moderate

A

1500 N
B

1000 N
C

2500 N
D

3500 N

Solution

Lift on the wing $= \frac{ρ}{2} A (v_{1}^{2} - v_{2}^{2}) = \frac{2}{2} \times 5 ({(30)}^{2} - {(20)}^{2})$
$= 5 \times 500 = 2500 N$

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