XLR105-5
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
Credit: Boeing / Rocketdyne
Rocketdyne LOx/Kerosene rocket engine. Atlas D. Atlas Sustainer. Gas generator, pump-fed. Shared turbopumps for booster engines. First flight 1958.
Thrust (sl): 252.700 kN (56,809 lbf). Thrust (sl): 25,771 kgf. Engine: 460 kg (1,010 lb). Chamber Pressure: 48.00 bar. Area Ratio: 25. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 80.5173913043478. Coefficient of Thrust vacuum: 1.73727457790893. Coefficient of Thrust sea level: 1.21644124457559.
Related
- Country
- USA
- Launch Vehicles
- Atlas Able, Atlas B, Atlas C, Atlas Centaur LV-3C, Atlas D, Atlas Agena A, Atlas LV-3B / Mercury
- Propellants
- Lox/Kerosene
- Agency
- Rocketdyne