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AJ10-118E
Part of AJ10
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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