RS-56-OSA

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RS-56-OSA

Part of LR105

Delta Engine In Test
Hot test firing of Delta RS-56 engine.

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

AKA: MA-5A. Status: Out of production. Date: 1988. Number: 63 . Thrust: 386.40 kN (86,866 lbf). Unfuelled mass: 460 kg (1,010 lb). Specific impulse: 316 s. Specific impulse sea level: 220 s. Burn time: 283 s. Height: 2.70 m (8.80 ft). Diameter: 3.05 m (10.00 ft).

Thrust (sl): 269.000 kN (60,473 lbf). Thrust (sl): 27,430 kgf. Engine: 460 kg (1,010 lb). Chamber Pressure: 48.00 bar. Area Ratio: 25. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 85.6521739130435. Oxidizer to Fuel Ratio: 2.25. Coefficient of Thrust vacuum: 1.77414206044677. Coefficient of Thrust sea level: 1.27414206044677.

Country: USA. Launch Vehicles: Atlas II, Atlas IIA, Atlas IIAS. Propellants: Lox/Kerosene. Stages: X-34A-1, Atlas IIA stage, Atlas II stage, Atlas IIAS stage. Agency: Rocketdyne.

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