This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
Used on stages: Saturn II-INT-17. Used on launch vehicles: Saturn INT-17. Propellants: Lox/LH2 Thrust(vac): 141,500 kgf. Thrust(vac): 1,387.00 kN. Isp: 450 sec. Isp (sea level): 360 sec. Chambers: 1. Country: USA. Status: Study 1966. Comments: Designation for high-performance high-pressure chamber Lox/LH2 engine developed from J-2, fitted with lower-expansion nozzle for seal level use on Saturn INT-17. Technology led to Space Shuttle Main Engines.
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Last update 12 March 2001.
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© Mark Wade, 2001 .