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MIT Rocket Team Home
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Liquid Propulsion Subteam
Project Romulus
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Romulus System Inputs
Created by
Alex Gale
, last modified on
Apr 17, 2024 12:44
Overall Characteristics
Formulas Used
Isp for matched nozzle:
Isp related to Cstar and Thrust Coefficient:
Thrust Coefficient:
Exit Velocity:
Thrust:
Compressible Mass flow and area ratio:
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{"serverDuration": 154, "requestCorrelationId": "0b59dd6a888e1930"}