RL-10A-4
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. Out of production. Centaur stage for Atlas IIA, Atlas IIAS. First flight 1992.
Engine: 168 kg (370 lb). Chamber Pressure: 39.12 bar. Area Ratio: 84. Thrust to Weight Ratio: 36.1735043478261. Oxidizer to Fuel Ratio: 5.5. Coefficient of Thrust vacuum: 1.74310161537244.
Related
- Country
- USA
- Launch Vehicles
- Atlas IIA, Atlas IIAS
- Propellants
- Lox/LH2
- Stages
- Centaur IIA
- Agency
- Pratt and Whitney