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HM-10
SEP, Ottobrunn LOx/LH2 rocket engine. Developed 1990's. Engine for potential Ariane 5 upper stage.

AKA: HM. Status: Developed 1990's. Thrust: 61.80 kN (13,893 lbf). Unfuelled mass: 145 kg (319 lb). Specific impulse: 443 s. Diameter: 1.00 m (3.20 ft).

Engine: 145 kg (319 lb). Chamber Pressure: 30.00 bar. Area Ratio: 61. Thrust to Weight Ratio: 43.448275862069. Coefficient of Thrust vacuum: 1.57922139504816. Coefficient of Thrust sea level: 0.



Country: France. Propellants: Lox/LH2. Agency: Ottobrunn.

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