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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 `70 ms^(-1) and 63 ms^(-1)` respectively. What is the lift on the wing if its area is` 2.5 m^(2)`? Take the density of air to be` 1.3 kg m^(-3)`

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Let `v_(1)` and `v_(2)` be the speeds of flow of air on the upper and the lower surfaces respectively of the wing of the aeroplane, and `P_(1)` and `P_(2)`
the corresponding air pressures. Then by Bernoulli.s theorem we have.
`P_(1)+(1)/(2)rho v_(1)^(2)=P_(2)+(1)/(2)rho v_(2)^(2)`
where, `rho` is the density of air. The pressure difference,
`P_(2)-P_(1)=(1)/(2)rho(v_(1)^(2)-v_(2)^(2))`
`rho=1.3" kg/m"^(3),v_(1)=70" m/s and "v_(2)=63" m/s"`
`:.P_(2)-P_(1)=(1)/(2)xx(1.3)[(70)^(2)-(63)^(2)]`
`=605" kg m"^(-2)s^(-2)=605" N/m"^(2)`
The difference of pressure provides the lift to the aeroplane.
`:.` Force of dynamic lift on the wing = pressure difference `xx` surface area of wing `=605xx2.5=1.5xx10^(3)N`
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