This page no longer updated from 31 October 2001. Latest version can be found at RD-224

Manufacturer Name: RD-224. Government Designation: 8D721. Designer: Glushko. Developed in: 1960-62. Application: R-26 stage 1. Used on stages: R-26 Stage 1. Used on launch vehicles: R-26. Propellants: Nitric acid/UDMH Thrust(vac): 181,306 kgf. Thrust(vac): 1,778.00 kN. Isp: 294 sec. Isp (sea level): 251 sec. Burn time: 100 sec. Mass Engine: 1,250 kg. Diameter: 2.3 m. Length: 2.0 m. Chambers: 4. Chamber Pressure: 83.40 bar. Area Ratio: 21.00. Oxidizer to Fuel Ratio: 2.50. Country: Russia. Status: Out of Production. First Flight: 1961. References: 320 . Comments: RD-224 is a block of 2 RD-225s. An upper stage thrust chamber was developed under designation U102-000.
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Last update 12 March 2001.
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