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RD-251
Part of RD-215

 RD-251
NPO Enerogmash Museum, November 1992
Credit: © Dietrich Haeseler
Glushko N2O4/UDMH rocket engine. R-36-0 stage 1, Tsyklon 2 stage 1. In production. Assembly of 3 RD-250-type units. First flight 1965.
 AKA: 8D723.  Status: In production.  Date: 1961-65.  Number:  131 . Thrust: 2,643.00 kN (594,170 lbf). Unfuelled mass: 1,729 kg (3,811 lb). Specific impulse: 301 s. Specific impulse sea level: 269 s. Burn time: 120 s. Height: 1.76 m (5.78 ft). Diameter: 2.52 m (8.26 ft). 
Chambers: 6. Thrust (sl): 2,366.000 kN (531,897 lbf). Thrust (sl): 241,300 kgf. Engine: 1,729 kg (3,811 lb). Chamber Pressure: 83.30 bar. Area Ratio: 14.7. Thrust to Weight Ratio: 156.15. Oxidizer to Fuel Ratio: 2.6. 
Family: 
Storable liquid. 
Country: 
Russia. 
Launch Vehicles: 
Tsiklon, 
R-36O 8K69, 
Tsiklon-2, 
R-36 8K67P. 
Propellants: 
N2O4/UDMH. 
Stages: 
R-36-1, 
R-36-0-1, 
Tsyklon 2-1. 
Agency: 
Glushko bureau. 
Bibliography: 
317, 
342, 
42. 
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