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|RD-219 - |
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Manufacturer Name: RD-219. Government Designation: 8D713. Other Designations: 11D26. Designer: Glushko. Developed in: 1958-61. Application: R-16 stage 2. Used on stages: R-16 Stage 2. Used on launch vehicles: R-16. Propellants: Nitric acid/UDMH Thrust(vac): 89,950 kgf. Thrust(vac): 883.00 kN. Isp: 293 sec. Burn time: 125 sec. Mass Engine: 760 kg. Diameter: 2.2 m. Length: 2.0 m. Chambers: 2. Chamber Pressure: 73.60 bar. Area Ratio: 25.80. Oxidizer to Fuel Ratio: 2.50. Country: Russia. Status: Hardware. First Flight: 1961. References: 225 , 317. 320 .
RD-219 is a derivative of RD-217 with a truss and some piping changes. Despite higher expansion ratio the engine is shorter than first stage engines. The result is relatively low performance, with Isp just 3 sec more than that of 1st stage in vacuum. Engine Cycle: Open. Feed Method: single turbopump feeding two gimballed chambers. Diameter is per chamber.
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Last update 12 March 2001.
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© Mark Wade, 2001 .