AJ10-118D
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
Aerojet Nitric acid/UDMH rocket engine. Used on Delta B, Delta C, Delta D upper stages. First flight 1962.
Engine: 90 kg (198 lb). Chamber Pressure: 7.00 bar. Area Ratio: 40. Propellant Formulation: RFNA/UDMH. Thrust to Weight Ratio: 38.1777777777778. Coefficient of Thrust vacuum: 13.7217788312386. Coefficient of Thrust sea level: 8.00749311695287.
Related
- Family
- Storable liquid
- Country
- USA
- Launch Vehicles
- Thor Delta B, Thor Delta D, Delta C
- Propellants
- Nitric acid/UDMH
- Stages
- Delta D
- Agency
- Aerojet