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Designer: Pratt and Whitney. Used on stages: Centaur B-X. Propellants: Lox/LH2 Thrust(vac): 9,524 kgf. Thrust(vac): 93.40 kN. Isp: 470 sec. Burn time: 408 sec. Mass Engine: 317 kg. Diameter: 1.5 m. Chambers: 1. Chamber Pressure: 102.04 bar. Area Ratio: 250.00. Thrust to Weight Ratio: 30.00. Country: USA. Status: Design concept 1994.
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Last update 12 March 2001.
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© Mark Wade, 2001 .