This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
Used on stages: X-34A-2. Propellants: Lox/Kerosene Thrust(vac): 4,500 kgf. Thrust(vac): 44.10 kN. Isp: 348 sec. Burn time: 325 sec. Diameter: 2.0 m. Chambers: 1. Country: USA. Status: Development -1996. Comments: NASA Marshall Space Flight Center prototype experimental engine that led to Fastrac low-cost engine for X-34.
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Last update 12 March 2001.
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© Mark Wade, 2001 .