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AJ10-118E
Part of AJ10 Family
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.

Number: 57 . Thrust: 35.10 kN (7,891 lbf). Unfuelled mass: 90 kg (198 lb). Specific impulse: 278 s. Burn time: 400 s. Diameter: 1.40 m (4.50 ft).

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.



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.

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