This page no longer updated from 31 October 2001.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

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.
Back to Index
Last update 12 March 2001.
Definitions of Technical Terms.
Contact Mark Wade with any corrections or comments.
Conditions for use of drawings, pictures, or other materials from this site..
© Mark Wade, 2001 .