LR91-7
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
Aerojet N2O4/Aerozine-50 rocket engine. Version used on Stage 2 of Gemini Titan 2 Launch Vehicle. Proposed for unflown Titan 3L2, Titan 3L4 boosters. First flight 1962.
Thrust (sl): 225.200 kN (50,627 lbf). Thrust (sl): 22,967 kgf. Engine: 565 kg (1,245 lb). Chamber Pressure: 50.00 bar. Area Ratio: 45. Thrust to Weight Ratio: 80.2814159292035. Oxidizer to Fuel Ratio: 1.79. Coefficient of Thrust vacuum: 2.07098641649344. Coefficient of Thrust sea level: 1.17098641649344.
Related
- Family
- Storable liquid
- Country
- USA
- Propellants
- N2O4/Aerozine-50
- Stages
- Titan 2-2, Titan LDC-2
- Agency
- Aerojet