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RD-251


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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. Back to top of page Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
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