Bell 8096

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Bell 8096

Part of Bell 8000

Agena in orbit
Credit: NASA

Bell Nitric acid/UDMH rocket engine. Out of production. Used in Agena stage on top of Thor, Atlas, and Titan launch vehicles. First flight 1963.

AKA: YLR81-BA. Status: Out of production. Number: 175 . Thrust: 71.20 kN (16,006 lbf). Unfuelled mass: 132 kg (291 lb). Specific impulse: 293 s. Burn time: 265 s. Diameter: 1.52 m (4.98 ft).

Engine: 132 kg (291 lb). Chamber Pressure: 35.00 bar. Area Ratio: 45. Propellant Formulation: RFNA/UDMH. Thrust to Weight Ratio: 54.9772727272727. Oxidizer to Fuel Ratio: 2.55. Coefficient of Thrust vacuum: .85. Restarts: 8.

Family: Storable liquid. Country: USA. Launch Vehicles: Thor SLV-2A Agena D, Atlas Agena D, Titan IIIB, Thorad SLV-2H Agena D, Titan 34B, Atlas F/Agena D. Propellants: Nitric acid/UDMH. Stages: Agena D. Agency: Bell.

Photo Gallery

Agena Engine
Credit: Bell

Hustler Engine
Credit: Bell

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