RL-10A-1
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. Version used on Atlas Centaur LV-3C, and proposed for various early Saturn launch vehicle designs. First flight 1961.
Engine: 131 kg (288 lb). Chamber Pressure: 24.00 bar. Area Ratio: 47. Thrust to Weight Ratio: 51.9389312977099. Coefficient of Thrust vacuum: 2.04916270983758. Coefficient of Thrust sea level: 9.08293765042492E-02.
Related
- Country
- USA
- Launch Vehicles
- Atlas Centaur LV-3C, Juno V-B, Saturn A-1, Saturn C-2, Saturn B-1, Saturn A-2, Saturn I
- Propellants
- Lox/LH2
- Stages
- Centaur C
- Agency
- Pratt and Whitney