XLR89-5
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. Designed for booster applications. Gas generator, pump-fed. Shared turbopumps for booster engines. First flight 1958.
Thrust (sl): 667.200 kN (149,993 lbf). Thrust (sl): 68,039 kgf. Engine: 643 kg (1,417 lb). Chamber Pressure: 40.00 bar. Area Ratio: 8. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 120.321928460342. Coefficient of Thrust vacuum: 1.73021886841794. Coefficient of Thrust sea level: 1.53021886841794.
Related
- Country
- USA
- Launch Vehicles
- Atlas Able, Atlas B, Atlas C, Atlas D, Atlas Agena A, Atlas LV-3B / Mercury
- Propellants
- Lox/Kerosene
- Stages
- Atlas MA-2
- Agency
- Rocketdyne