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 =(Plower−Pupper)A
According to Bernoulli's Theorem =(12ρv2upper−12ρv2lower)A =12ρA[(√2v)2−v2]=12ρAv2