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RD-0124M1
Part of RD-0106
Kosberg LOx/Kerosene rocket engine. Developed 1998-. Proposed single chamber variant of RD-0124. Obviously same turbopumps, but one single chamber with larger nozzle extension compared to RD-0124M.

Status: Developed 1998-. Date: 1998-. Thrust: 294.30 kN (66,161 lbf). Unfuelled mass: 393 kg (866 lb). Specific impulse: 359 s. Burn time: 300 s. Height: 2.60 m (8.50 ft). Diameter: 1.50 m (4.90 ft).

Engine: 393 kg (866 lb). Chamber Pressure: 157.00 bar. Thrust to Weight Ratio: 76.33.

Country: Russia. Propellants: Lox/Kerosene. Agency: Kosberg bureau.
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