TR-201
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
TRW N2O4/Aerozine-50 rocket engine. Apollo lunar module ascent stage engines. Surplus engines used on Delta P stage. First flight 1972.
Engine: 113 kg (249 lb). Chamber Pressure: 7.00 bar. Area Ratio: 46. Thrust to Weight Ratio: 31.4338235294118. Oxidizer to Fuel Ratio: 1.59. Coefficient of Thrust vacuum: 1.45719168532336.
Related
- Family
- Storable liquid
- Country
- USA
- Spacecraft
- Apollo LM
- Launch Vehicles
- Delta 2000, Delta 3000
- Propellants
- N2O4/Aerozine-50
- Stages
- Delta P
- Agency
- TRW