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 $1.51 \times 10^{3} \;N$.