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 $70 \; m s^{-1}$ and $63 \; m s^{-1}$ respectively. What is the lift on the wing if its area is $2.5 \; m^{2}$? Take the density of air to be $1.3 \; kg m^{-3}$.

• A
  $1.51 \times 10^{3} \; N$
• B
  $3.64 \times 10^{4} \; N$
• C
  $2.67 \times 10^{5} \; N$
• D
  $8.60 \times 10^{2} \; N$