LR87-7
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
Aerojet N2O4/Aerozine-50 rocket engine. Study 1961. Version of LR-87-5 used on Gemini Titan 2 launch vehicle. Proposed for unflown Titan 3L2, Titan 3L4 boosters. First flight 1962.
Thrust (sl): 946.700 kN (212,827 lbf). Thrust (sl): 96,535 kgf. Engine: 713 kg (1,571 lb). Chamber Pressure: 47.00 bar. Area Ratio: 9. Thrust to Weight Ratio: 155.333800841515. Oxidizer to Fuel Ratio: 1.9. Coefficient of Thrust vacuum: 2.2310677081288. Coefficient of Thrust sea level: 1.97574855919263.
Related
- Family
- Storable liquid
- Country
- USA
- Propellants
- N2O4/Aerozine-50
- Stages
- Titan 2-1, Titan LDC-1
- Agency
- Aerojet