RL-10A-3
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
Credit: Lockheed Martin
Pratt and Whitney LOx/LH2 rocket engine. First flight 1967.
Engine: 131 kg (288 lb). Chamber Pressure: 28.00 bar. Area Ratio: 57. Thrust to Weight Ratio: 51.0725190839695. Oxidizer to Fuel Ratio: 5. Coefficient of Thrust vacuum: 1.72712561226611.
Related
- Country
- USA
- Spacecraft
- Apollo Direct RM
- Launch Vehicles
- Atlas Centaur LV-3C, Titan 3BAS2, Atlas Centaur D, Saturn IB-A, Saturn IB-CE, Titan 3L2, Titan 3L4, Saturn V-Centaur, Titan IIIE
- Propellants
- Lox/LH2
- Stages
- Centaur D/E
- Agency
- Pratt and Whitney