This page no longer updated from 31 October 2001. Latest version can be found at S-3

S-3B engine
S-3B engine -

Credit: USAF. 30,038 bytes. 197 x 444 pixels.

Designer: Rocketdyne. Used on stages: Jupiter, Jupiter Cluster. Used on launch vehicles: Juno II, Saturn A-2. Propellants: Lox/Kerosene Thrust(vac): 77,367 kgf. Thrust(vac): 758.70 kN. Isp: 282 sec. Isp (sea level): 248 sec. Burn time: 182 sec. Mass Engine: 725 kg. Diameter: 2.7 m. Chambers: 1. Chamber Pressure: 39.50 bar. Area Ratio: 8.00. Thrust to Weight Ratio: 106.71. Country: USA. Status: Out of Production. First Flight: 1958. Last Flight: 1961. Flown: 10.
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Last update 12 March 2001.
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© Mark Wade, 2001 .