RS-56-OSA
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
Hot test firing of Delta RS-56 engine.
Rocketdyne LOx/Kerosene rocket engine. Out of production. Designed for booster applications. Gas generator, pump-fed. Sustainer engine for Atlas II, IIA, IIAS. First flight 1991.
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: 1.77414206044677. Coefficient of Thrust sea level: 1.27414206044677.
Related
- Country
- USA
- Launch Vehicles
- Atlas II, Atlas IIA, Atlas IIAS
- Propellants
- Lox/Kerosene
- Agency
- Rocketdyne