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Propellants: N2O4/MMH Thrust(vac): 1,814 kgf. Thrust(vac): 17.80 kN. Isp: 300 sec. Mass Engine: 41 kg. Diameter: 0.7 m. Chambers: 1. Area Ratio: 98.00. Thrust to Weight Ratio: 44.34. Country: USA. Status: Design concept 1960's. Comments: 1960's designs for 'big dumb booster'..
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Last update 12 March 2001.
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© Mark Wade, 2001 .