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RD-0139
Part of RD-0120
Kosberg LOx/LNG rocket engine. stage 1. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Gas generator cycle with turbine gas injection into supersonic nozzle.

Status: Developed 1998-on. Date: 1998-. Thrust: 2,038.00 kN (458,160 lbf). Unfuelled mass: 1,544 kg (3,403 lb). Specific impulse: 341 s. Specific impulse sea level: 301 s. Height: 3.61 m (11.84 ft).

Engine: 1,544 kg (3,403 lb). Thrust to Weight Ratio: 134.58.

Country: Russia. Propellants: Lox/LNG. Agency: Kosberg bureau. Bibliography: 403.
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