In a test experiement on a model aeroplane in a wind tunnel, the flow speeds on the lower and upper surfaces of the wing are `upsilon` and `upsilonsqrt(2)` respectively. If the density of air is `rho` and the surface area of the wings is A, what is the dynamic lift on the wing of aeroplane.

Explanation

Ler `P_(1)` and `P_(2)` be the air pressure on the upper and lower surface of the wing. Using Bernoulli's theorem, we have ,
`P_(1)+1/2 rho upsilon_(1)^(2) = p_(2)+1/2 rho upsilon_(2)^(2)`
`:. P_(1)-P_(2)=1/2 rho (upsilon_(2)^(2)-upsilon_(1)^(2))`
`= 1/2 rho (2upsilon^(2) - upsilon^(2)) = 1/2 rho upsilon^(2)`
`:.` The force of dynamic lift = `(P_(1)-P_(2)) xx A`
`=1/2 rho upsilon^(2) xxA`.