RD-219
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Credit: © Mark Wade
Glushko Nitric acid/UDMH rocket engine. R-16 stage 2. Derivative of RD-217 with a truss and piping changes. Despite higher expansion ratio, engine was shorter than first stage version, with relatively low performance. Flown 1960-1972.
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 gimbaled chambers. Diameter is per chamber.
Chambers: 2. Engine: 760 kg (1,670 lb). Chamber Pressure: 73.60 bar. Area Ratio: 25.8. Propellant Formulation: AK27I/UDMH. Thrust to Weight Ratio: 118.35. Oxidizer to Fuel Ratio: 2.5.
Related
- Family
- Storable liquid
- Country
- Russia
- Launch Vehicles
- R-16
- Propellants
- Nitric acid/UDMH
- Stages
- R-16-2
- Agency
- Glushko bureau