RL-10 RL-10 Credit - Lockheed Martin Designer: Pratt and Whitney. Propellants: Lox/LH2. Thrust(vac): 66.700 kN (14,995 lbf). Isp: 410 sec. Isp (sea level): 10 sec. Burn time: 482 sec. Mass Engine: 131 kg (288 lb). Diameter: 0.92 m (3.00 ft). Chambers: 1. Chamber Pressure: 24.00 bar. Area Ratio: 40.00. Thrust to Weight Ratio: 44.63. Country: USA. First Flight: 1961. Last Flight: 1965. Flown: 60. RL-10 used on Rocket Stages Used on stage: Nova A-3. on launch vehicle: Nova A. Used on stage: Nova B-3. on launch vehicle: Nova B. Used on stage: Saturn IV. on launch vehicle: Saturn B-1. Used on stage: Saturn IV. on launch vehicle: Saturn C-2. Used on stage: Saturn IV. on launch vehicle: Saturn C-3. Used on stage: Saturn IV. on launch vehicle: Saturn I.                   Contact us with any corrections, additions, or comments. Conditions for use of drawings, pictures, or other materials from this site.. To contact astronauts or cosmonauts. © Mark Wade, 1997 - 2007 except where otherwise noted.

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