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AJ10-118D
Part of AJ10 Family
Aerojet Nitric acid/UDMH rocket engine. Used on Delta B, Delta C, Delta D upper stages. First flight 1962.

Number: 24 . Thrust: 33.70 kN (7,576 lbf). Unfuelled mass: 90 kg (198 lb). Specific impulse: 278 s. Burn time: 170 s. Diameter: 0.84 m (2.75 ft).

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.



Family: Storable liquid. Country: USA. Launch Vehicles: Thor Delta B, Thor Delta D, Delta C. Propellants: Nitric acid/UDMH. Stages: Delta D. Agency: Aerojet.

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