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RD-251
Credit - © Dietrich Haeseler
Engine Model: RD-251. Manufacturer Name: RD-251. Government Designation: 8D723. Designer: Glushko. Developed in: 1961-65. Application: R-36-0 stage 1, Tsyklon 2 stage 1. Propellants: N2O4/UDMH. Thrust(vac): 2,643.000 kN (594,170 lbf). Thrust(sl): 2,366.000 kN (531,897 lbf). Isp: 301 sec. Isp (sea level): 269 sec. Burn time: 120 sec. Mass Engine: 1,729 kg (3,811 lb). Diameter: 2.52 m (8.26 ft). Length: 1.76 m (5.78 ft). Chambers: 6. Chamber Pressure: 83.30 bar. Area Ratio: 14.70. Oxidizer to Fuel Ratio: 2.60. Thrust to Weight Ratio: 156.15. Country: Russia. Status: In production. First Flight: 1965. Last Flight: 2006. Flown: 131.

Assembly of 3 RD-250-type units.

RD-251 used on Rocket Stages
Bibliography:

  • Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991 (succeeded by 2000 edition).
  • Haeseler, Dietrich, Information from NPO Energomash museum exhibit, Nov. 1992 via Dietrich Haeseler.
  • Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
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© Mark Wade, 1997 - 2008 except where otherwise noted.