This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
Used on stages: A-4. Used on launch vehicles: V-2. Propellants: Lox/Alcohol Thrust(vac): 31,800 kgf. Thrust(vac): 311.80 kN. Isp: 239 sec. Isp (sea level): 203 sec. Burn time: 68 sec. Mass Engine: 931 kg. Diameter: 0.8 m. Chambers: 1. Chamber Pressure: 15.00 bar. Area Ratio: 3.29. Thrust to Weight Ratio: 34.16. Country: Germany. Status: Out of Production. First Flight: 1944. Last Flight: 1963. Flown: 25000.
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Last update 12 March 2001.
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© Mark Wade, 2001 .