The formula to calculate the Thrust is:
\[ T = v \times \left(\frac{dm}{dt}\right) \]
Where:
Thrust is defined as the total force generated by the exhaust of burning fuel in a rocket.
Let's assume the following values:
Using the formula:
\[ T = 3000 \times 0.5 = 1500 \, \text{N} \]
The Thrust is approximately 1500 N.
