LR89-5
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. Designed for booster applications. Gas generator, pump-fed. Separate turbopumps for each booster engine. First flight 1960.
Thrust (sl): 726.000 kN (163,211 lbf). Thrust (sl): 74,037 kgf. Engine: 720 kg (1,580 lb). Chamber Pressure: 41.00 bar. Area Ratio: 8. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 116.486111111111. Oxidizer to Fuel Ratio: 2.25. Coefficient of Thrust vacuum: 1.42466495026104. Coefficient of Thrust sea level: 1.22954299904152.
Related
- Country
- USA
- Spacecraft
- Ames Mach 10 Demonstrator
- Launch Vehicles
- Atlas Centaur LV-3C, Atlas E, Saturn B-1, Atlas Agena B, Atlas F, Atlas Agena D, Atlas SLV-3
- Propellants
- Lox/Kerosene
- Stages
- Titan Cluster, Atlas MA-3
- Agency
- Rocketdyne