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LR79-7
Part of LR79 Family
MB-1/MB-3
MB-1/MB-3
Credit: © Mark Wade
Rocketdyne LOx/Kerosene rocket engine. Out of production. Designed for booster applications. Gas generator, pump-fed. First flight 1957.

AKA: LR79--NA-7;MB-1. Status: Out of production.. Date: 1955. Number: 268 . Thrust: 758.70 kN (170,563 lbf). Specific impulse: 282 s. Specific impulse sea level: 248 s. Burn time: 165 s. Diameter: 1.53 m (5.00 ft).

Thrust (sl): 667.200 kN (149,993 lbf). Thrust (sl): 68,039 kgf. Engine: 643 kg (1,417 lb). Chamber Pressure: 41.00 bar. Area Ratio: 8. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 120.321928460342. Coefficient of Thrust vacuum: 1.25036300393336. Coefficient of Thrust sea level: 1.05524105271385.



Country: USA. Launch Vehicles: Thor, Delta, Thor Able, Thor Agena A, Thor Agena B, Thor Agena D, Thor Burner. Propellants: Lox/Kerosene. Stages: Thor DM-19. Agency: Rocketdyne.
Photo Gallery

LR-79 EngineLR-79 Engine
Credit: Bob Fortune



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