This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
Designer: Rocketdyne. Used on stages: Saturn II-SL. Used on launch vehicles: Saturn INT-19. Propellants: Lox/LH2 Thrust(vac): 101,634 kgf. Thrust(vac): 996.70 kN. Isp: 390 sec. Isp (sea level): 275 sec. Burn time: 310 sec. Mass Engine: 1,360 kg. Chambers: 1. Chamber Pressure: 30.00 bar. Area Ratio: 14.00. Country: USA. Status: Study 1966. Comments: Sea level version of J-2 with reduced expansion ratio proposed for Saturn II first stage use.
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 .