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Propellants: N2O4/MMH Thrust(vac): 2,039 kgf. Thrust(vac): 20.00 kN. Isp: 347 sec. Mass Engine: 58 kg. Diameter: 0.8 m. Length: 1.7 m. Chambers: 1. Chamber Pressure: 88.80 bar. Area Ratio: 400.00. Oxidizer to Fuel Ratio: 1.86. Thrust to Weight Ratio: 35.15. Country: USA. Status: Developed 1990's. Comments: Advance technology engine for maneuvering stages.
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Last update 12 March 2001.
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© Mark Wade, 2001 .