RL-10A-3A
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. Used on Centaur stage atop Atlas G, Atlas I, Atlas II, Titan 4. First flight 1984.
Engine: 141 kg (310 lb). Chamber Pressure: 32.31 bar. Area Ratio: 61. Thrust to Weight Ratio: 53.2400806451613. Oxidizer to Fuel Ratio: 5. Coefficient of Thrust vacuum: 1.67432171823688.
Related
- Country
- USA
- Spacecraft
- Space Tug
- Launch Vehicles
- Atlas G Centaur, Titan 4, Atlas I, Atlas II
- Propellants
- Lox/LH2
- Stages
- Centaur G, Centaur I, Centaur II, Centaur G STS, Centaur G Prime
- Agency
- Pratt and Whitney