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You are a propulsion engineer tasked with selecting a suitable chamber material ...
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You are a propulsion engineer tasked with selecting a suitable chamber material for a new rocket engine with performance characteristics similar to SpaceX's Merlin engines. To ensure the structural integrity of the combustion chamber, you need to determine the operating pressure it will experience.
Using the following engine parameters, calculate the chamber pressure:
- c* = 1800 m/s (Characteristic velocity)
- Mass flow rate: 1500 kg/s
- Thrust coefficient: 1.8
- Throat area: 0.6 m²
- g0 = 9.81 m/s²
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