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In a test experiment on a model aeroplan...

In a test experiment on a model aeroplane in a wind tunnel, the flow speeds on the upper and lower surfaces of the wing are `70ms^(-1)` and `83ms^(-1)` respectively. What is the lift on the wing, if its area is `2.5m^(2)`? Take the density of air to be `1.3kgm^(-3)`

A

1513 N

B

1513 dynes

C

151.3 N

D

151.3 dynes

Text Solution

Verified by Experts

The correct Answer is:
A
`F=(P_(2)-P_(1))A, P_(2)-P_(1)=(1)/(2)rho(v_(1)^(2)-v_(2)^(2))`
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