This page no longer updated from 31 October 2001. Latest version can be found at RD-216

Manufacturer Name: RD-216. Government Designation: 11D614. Designer: Glushko. Developed in: 1958-60. Application: R-14, Kosmos 11K63 stage 1. Used on stages: Kosmos-1. Used on launch vehicles: Kosmos 11K65, Kosmos 11K65M, Kosmos 65MP, Kosmos 65S3. Propellants: Nitric acid/UDMH Thrust(vac): 177,400 kgf. Thrust(vac): 1,728.00 kN. Isp: 291 sec. Isp (sea level): 248 sec. Burn time: 146 sec. Mass Engine: 1,350 kg. Diameter: 2.3 m. Length: 2.2 m. Chambers: 4. Chamber Pressure: 73.60 bar. Area Ratio: 18.80. Oxidizer to Fuel Ratio: 2.50. Country: Russia. Status: In Production. First Flight: 1964. Last Flight: 1999. Flown: 441. References: 225 , 287 , 42 , 317 , 320 .

RD-216 is a block of 2 RD-215's. The RD-216 had 2 combustion chambers and 2 turbines. Two sets of these were used in the first stage of the R-14 missile and Kosmos 11K63 series launch vehicles. Beginning with this engine Glushko cut the previous 3 to 5 year development time for new engines to 2 years. Diameter is per chamber.

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Last update 12 March 2001.
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