To find the thrust of the rocket engine, we can use the thrust equation, which is given by:
\[
F = \dot{m} \cdot v + (P_e - P_a) \cdot A_e
\]
Where:
- \( F \) is the thrust,
- \( \dot{m} \) is the mass flow rate,
- \( v \) is the velocity of the exhaust gases,
-
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