LR91-5
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
Aerojet N2O4/Aerozine-50 rocket engine. Titan 2 ICBM Stage 2. Out of Production. Scaled down version of stage 1 engine featuring fixed single chamber. Gas generator cycle. First flight 1962.
Propellant flow rate: 163 kg/sec. Mixture Ratio: 1.80.
Engine: 500 kg (1,100 lb). Chamber Pressure: 56.20 bar. Area Ratio: 49.2. Thrust to Weight Ratio: 90.71. Oxidizer to Fuel Ratio: 1.8.
Related
- Family
- Storable liquid
- Country
- USA
- Launch Vehicles
- Titan II
- Propellants
- N2O4/Aerozine-50
- Agency
- Aerojet