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Engine · USA

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Rocketdyne N2O4/MMH rocket engine. Developed 1990's. Advance technology engine for maneuvering stages.

Engine: 58 kg (127 lb). Chamber Pressure: 88.80 bar. Area Ratio: 400. Thrust to Weight Ratio: 35.1506204084502. Oxidizer to Fuel Ratio: 1.86. Coefficient of Thrust vacuum: 1.93961344573183. Coefficient of Thrust sea level: 0.

Family: Storable liquid
Country: USA
Propellants: N2O4/MMH
Agency: Rocketdyne

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