Question

The thrust produced by a rocket is 150,000 N, and the mass flow rate is 50,000 kg/s. What is the exhaust velocity of the rocket?


5 m/s


3 m/s


4 m/s


6 m/s

Answer 1

To find the exhaust velocity of the rocket, we can use the thrust equation:

\[
\text{Thrust} = \text{mass flow rate} \times \text{exhaust velocity}
\]

Given:
- Thrust = 150,000 N
- Mass flow rate = 50,000 kg/s

We can rearrange the equation to solve for exhaust velocity (\(v_e\)):

\[
v_e = \frac{\text{Thrust}}{\text{mass flow rate}}
\]

Substituting the given values:

\[
v_e = \frac{150,000 \, \text{N}}{50,000 \, \text{kg/s}} = 3 \, \text{m/s}
\]

Therefore, the exhaust velocity of the rocket is **3 m/s**.