LR89-7
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 space launchers. Out of production. Designed for booster applications. Gas generator, pump-fed. Shared turbopumps for booster engines. Evolved from MA-2 ICBM system. First flight 1963.
Thrust (sl): 835.100 kN (187,738 lbf). Thrust (sl): 85,162 kgf. Engine: 712 kg (1,569 lb). Chamber Pressure: 42.00 bar. Area Ratio: 8. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 135.867884750527. Oxidizer to Fuel Ratio: 2.25. Coefficient of Thrust vacuum: 1.53013234508252. Coefficient of Thrust sea level: 1.34831416326433.
Related
- Country
- USA
- Launch Vehicles
- Atlas Centaur LV-3C, Atlas Agena D, Atlas Centaur D, Atlas F/Agena D, Atlas H, Atlas G Centaur, Atlas I
- Propellants
- Lox/Kerosene
- Stages
- Atlas MA-5
- Agency
- Rocketdyne