First slide

Fluid dynamics

Question

Air streams horizontally across an aeroplane wing of area $4 m^{2}$ weighing $500 k g$ . The air speed is $70 m / s$ and $50 m / s$ 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

$4000 N$
B

$3500 N$
C

$5270 N$
D

$6206 N$

Solution

$F = (p_{1} - p_{2}) A = \frac{1}{2} ρ (V_{2}^{2} - V_{1}^{2}) A = \frac{1}{2} 1.293 (4900 - 2500) \times 4 = 6206 N$

Get Instant Solutions

When in doubt download our app. Now available Google Play Store- Doubts App

Recieve an sms with download link

Doubts App

OR

SCAN ME

Doubts App

Doubts App