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Designer: SEP. Propellants: Lox/LH2 Thrust(vac): 6,300 kgf. Thrust(vac): 61.80 kN. Isp: 443 sec. Mass Engine: 145 kg. Diameter: 1.0 m. Chambers: 1. Chamber Pressure: 30.00 bar. Area Ratio: 61.00. Thrust to Weight Ratio: 43.45. Country: France. Status: Developed 1990's. Comments: Engine for potential Ariane 5 upper stage.
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Last update 12 March 2001.
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© Mark Wade, 2001 .