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RD-56
Isayev LOx/LH2 rocket engine. N1 block R. Development ended 1971. Oxygen-hydrogen engine for cryogenic upper stage. Developed but never flown. Design sold to India in 1990's for GSLV.

AKA: 11D56;D-56;KVD-1;KVD-1, D-56. Status: Development ended 1971. Date: 1960-77. Thrust: 69.60 kN (15,647 lbf). Unfuelled mass: 282 kg (621 lb). Specific impulse: 462 s. Burn time: 800 s. Height: 2.14 m (7.02 ft). Diameter: 1.56 m (5.11 ft).

Engine: 282 kg (621 lb). Chamber Pressure: 55.90 bar. Area Ratio: 198.7. Thrust to Weight Ratio: 25.17. Oxidizer to Fuel Ratio: 6.

Subtopics
RD-56M Isayev LOx/LH2 rocket engine. Originally developed for Proton and Angara upper stage KVRB with planned first flight 1995. Finally flown on 12KRB upper stage for India's GSLV. First flight 2001.
RD-56M LNG Isayev LOx/LNG rocket engine. Vozdushnyy Start stage 2. Developed 1996-. Variant of RD-56M using liquid natural gas in place of hydrogen. First engine tests performed in 1998.
Country: Russia. Launch Vehicles: N1M, N1F-L3M. Propellants: Lox/LH2. Stages: N1 Block R. Agency: Isayev bureau. Bibliography: 225, 227, 314, 327, 342, 344, 89, 93.
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