This page no longer updated from 31 October 2001. Latest version can be found at PF RP-1

Used on stages: Saturn LCB-Lox/RP-1. Used on launch vehicles: Saturn LCB-Lox/RP-1. Propellants: Lox/Kerosene Thrust(vac): 2,070,700 kgf. Thrust(vac): 20,306.00 kN. Isp: 275 sec. Isp (sea level): 253 sec. Burn time: 163 sec. Chambers: 1. Country: USA. Status: Design concept 1960's.
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 .