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RS-56-OBA
Part of LR79 Family

Hot Fire Test 72

Hot Fire Test 72
Hot firing test of Atlas rocket engine.

Rocketdyne LOx/Kerosene rocket engine. Out of production. Designed for booster applications. Gas generator, pump-fed. Booster engine for Atlas II, IIA, IIAS. First flight 1991.

Status: Out of production. Date: 1988. Number: 126 . Thrust: 1,046.80 kN (235,330 lbf). Unfuelled mass: 805 kg (1,774 lb). Specific impulse: 299 s. Specific impulse sea level: 263 s. Burn time: 172 s. Height: 3.43 m (11.25 ft). Diameter: 2.45 m (8.03 ft).

Thrust (sl): 920.800 kN (207,004 lbf). Thrust (sl): 93,897 kgf. Engine: 805 kg (1,774 lb). Chamber Pressure: 48.00 bar. Area Ratio: 8. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 132.298136645963. Oxidizer to Fuel Ratio: 2.25. Coefficient of Thrust vacuum: 1.545. Coefficient of Thrust sea level: 1.37.



Country: USA. Launch Vehicles: Atlas II, Atlas IIA, Atlas IIAS. Propellants: Lox/Kerosene. Stages: Atlas MA-5A, Atlas MA-5AS. Agency: Rocketdyne.

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