LR91-3
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
Aerojet LOx/Kerosene rocket engine. Development begun 1957. Titan 1 Stage 2 major production version. Proposed for second stage of Juno V-A, Super-Jupiter in 1959. Flown 1959-1965.
Thrust (sl): 242.600 kN (54,539 lbf). Thrust (sl): 24,742 kgf. Engine: 590 kg (1,300 lb). Chamber Pressure: 45.00 bar. Area Ratio: 25. Thrust to Weight Ratio: 61.5050847457627. Coefficient of Thrust vacuum: 1.84091739925958. Coefficient of Thrust sea level: 1.28536184370403.
Related
- Country
- USA
- Launch Vehicles
- Titan I, Super-Jupiter, Juno V-A
- Propellants
- Lox/Kerosene
- Stages
- Titan 1-2
- Agency
- Aerojet