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

Status: Developed 1990's. Thrust: 20.00 kN (4,496 lbf). Unfuelled mass: 58 kg (127 lb). Specific impulse: 347 s. Height: 1.72 m (5.64 ft). Diameter: 0.76 m (2.51 ft).

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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