In a test experiment on a model aeroplane in a wind tunnel, the flow speeds on the upper and lower surface of the wing are `70 ms^(-1) and 63 ms^(-1)` respectivley. What is the lift on the wing if its area is `2.5 m^(2)`? Take the density of air is `1.3 kg m^(-3)`.

Explanation

To solve the problem of calculating the lift on the wing of a model aeroplane in a wind tunnel, we will use Bernoulli's principle, which relates the pressure difference between the upper and lower surfaces of the wing to the velocities of the airflow over those surfaces.

### Step-by-Step Solution:

1. **Identify Given Data:**
- Velocity on the upper surface, \( V_1 = 70 \, \text{m/s} \)
- Velocity on the lower surface, \( V_2 = 63 \, \text{m/s} \)
- Area of the wing, \( A = 2.5 \, \text{m}^2 \)
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