To determine the mass flow rate ($\dot{m}$) of the exhaust gases, we use the thrust equation:

$F = \dot{m} \cdot v_e$

Where:

• $F$ is the thrust (in Newtons, $N$)
• $\dot{m}$ is the mass flow rate (in $\text{kg/s}$)
• $v_e$ is the exhaust velocity (in $\text{m/s}$)

Rearranging for $\dot{m}$:

$\dot{m} = \frac{F}{v_e}$

Substituting the given values:

$F = 70,000 \, \text{N}, \quad v_e = 3,000 \, \text{m/s}$ $\dot{m} = \frac{70,000}{3,000}$

Calculating:

$\dot{m} = 23.33 \, \text{kg/s}$

The closest answer is:
D) 23.3 kg/s

---

Would you like a detailed explanation of the process? Let me know if you have more questions!

Related Questions:

1. What is the physical significance of the exhaust velocity in a rocket?
2. How does the thrust equation change if gravity is included?
3. How can we derive the thrust equation from the conservation of momentum principle?
4. What factors affect the exhaust velocity in a rocket engine?
5. What are the real-world applications of the thrust and mass flow rate relationship?

Tip:

The mass flow rate ($\dot{m}$) is crucial for calculating fuel efficiency and determining how long a rocket can sustain its thrust during operation.