LR105-5
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 E, F. Atlas Sustainer. Gas generator, pump-fed. Separate turbopumps for each booster engine. First flight 1960.
Thrust (sl): 269.000 kN (60,473 lbf). Thrust (sl): 27,430 kgf. Engine: 460 kg (1,010 lb). Chamber Pressure: 48.00 bar. Area Ratio: 25. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 85.6521739130435. Oxidizer to Fuel Ratio: 2.25. Coefficient of Thrust vacuum: 1.84806464629871. Coefficient of Thrust sea level: 1.32723131296538.
Related
- Country
- USA
- Launch Vehicles
- Atlas Centaur LV-3C, Atlas E, Atlas Agena B, Atlas F, Atlas Agena D, Atlas Centaur D, Atlas SLV-3
- Propellants
- Lox/Kerosene
- Agency
- Rocketdyne