Explanation:
This problem is solved using Bernoulli's equation.
Let [tex]P[/tex] be the pressure at a point.
Let [tex]p[/tex] be the density fluid at a point.
Let [tex]v[/tex] be the velocity of fluid at a point.
Bernoulli's equation states that [tex]P+\frac{1}{2}pv^{2}+pgh=constant[/tex] for all points.
Lets apply the equation of a point just above the wing and to point just below the wing.
Let [tex]p_{up}[/tex] be the pressure of a point just above the wing.
Let [tex]p_{do}[/tex] be the pressure of a point just below the wing.
Since the aeroplane wing is flat,the heights of both the points are same.
[tex]\frac{1}{2}(1.29)(255)^{2}+p_{up}= \frac{1}{2}(1.29)(199)^{2}+p_{do}[/tex]
So,[tex]p_{up}-p_{do}=\frac{1}{2}\times 1.29\times (25424)=16398.48Pa[/tex]
Force is given by the product of pressure difference and area.
Given that area is [tex]27ms^{2}[/tex].
So,lifting force is [tex]16398.48\times 27=442758.96N[/tex]
