AJ10-118E
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 E, Delta G, Delta J, Delta L, Delta M, Delta N upper stages. First flight 1965.
Engine: 90 kg (198 lb). Chamber Pressure: 7.00 bar. Area Ratio: 40. Propellant Formulation: RFNA/UDMH. Thrust to Weight Ratio: 39.7666666666667. Coefficient of Thrust vacuum: 5.14542744974419.
Related
- Family
- Storable liquid
- Country
- USA
- Launch Vehicles
- N, Thor Delta E, Thor Delta G, Thor Delta J, Thor Delta N, Thor Delta M, Thor Delta L
- Propellants
- Nitric acid/UDMH
- Stages
- Delta E
- Agency
- Aerojet