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Question

The flow speeds of air on the lower and upper surfaces of the wing of an aeroplane are v and 2v respectively. The density of air is ρ and surface area of wing is A. The dynamic lift on the wing is:

A
ρv2A
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B
2ρv2A
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C
(12)ρv2A
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D
2ρv2A
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Solution

The correct option is C (12)ρv2A
Dynamic lift = Pressure difference × Area
=(PlowerPupper)A
According to Bernoulli's Theorem
=(12ρv2upper12ρv2lower)A
=12ρA[(2v)2v2]=12ρAv2

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