LR79-7
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
Credit: © Mark Wade
Rocketdyne LOx/Kerosene rocket engine. Out of production. Designed for booster applications. Gas generator, pump-fed. First flight 1957.
Thrust (sl): 667.200 kN (149,993 lbf). Thrust (sl): 68,039 kgf. Engine: 643 kg (1,417 lb). Chamber Pressure: 41.00 bar. Area Ratio: 8. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 120.321928460342. Coefficient of Thrust vacuum: 1.25036300393336. Coefficient of Thrust sea level: 1.05524105271385.
Related
- Country
- USA
- Launch Vehicles
- Thor, Delta, Thor Able, Thor Agena A, Thor Agena B, Thor Agena D, Thor Burner
- Propellants
- Lox/Kerosene
- Stages
- Thor DM-19
- Agency
- Rocketdyne
Photo Gallery
LR-79 Engine
Credit: Bob Fortune
