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.
|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.|