Engine Model: RD-219. Manufacturer Name: RD-219. Government Designation: 8D713. Other Designations: 11D26. Designer: Glushko. Developed in: 1958-61. Application: R-16 stage 2. Propellants: Nitric acid/UDMH. Thrust(vac): 883.000 kN (198,506 lbf). Isp: 293 sec. Burn time: 125 sec. Mass Engine: 760 kg (1,670 lb). Diameter: 2.16 m (7.08 ft). Length: 2.03 m (6.66 ft). Chambers: 2. Chamber Pressure: 73.60 bar. Area Ratio: 25.80. Oxidizer to Fuel Ratio: 2.50. Thrust to Weight Ratio: 118.35. Country: Russia. First Flight: 1960. Last Flight: 1972. Flown: 212. 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.
RD-219 used on Rocket Stages
Bibliography:- Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993.
- Haeseler, Dietrich, Information from NPO Energomash museum exhibit, Nov. 1992 via Dietrich Haeseler.
- Glushko, V P, Albom Konstruktsiy ZhRD, Vol. 1 1968, Vol. 3 & 4 1969 via Dietrich Haeseler.
