a
Speed of wind on the upper surface of the wing, \(V_{1}=70 m / s\) Speed of wind on the lower surface of the wing, \(V_{2}=63 m / s\) Area of the wing, \(A=2.5 m ^{2}\) Density of air, \(\rho=1.3 kg m ^{-3}\)

According to Bernoulli's theorem, we have the relation:

\(P_{1}+\frac{1}{2} \rho V_{1}^{2}=P_{2}+\frac{1}{2} \rho V_{2}^{2}\)

\(P_{2}-P_{1}=\frac{1}{2} \rho\left(V_{1}^{2}-V_{2}^{2}\right)\)

Where,

\(P_{1}=\) Pressure on the upper surface of the wing

\(P_{2}=\) Pressure on the lower surface of the wing

The pressure difference between the upper and lower surfaces of the wing provides lift to the aeroplane.

Lift on the wing \(=\left(P_{2}-P_{1}\right) A\)

\(=\frac{1}{2} \rho\left(V_{1}^{2}-V_{2}^{2}\right) A\)

\(=\frac{1}{2} 1.3\left((70)^{2}-(63)^{2}\right) \times 2.5\)

\(=1512.87\)

\(=1.51 \times 10^{3} N\)

Therefore, the lift on the wing of the aeroplane is \(1.51 \times 10^{3} \;N\).