RD-219

Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z

RD-219

Part of RD-215

RD-219
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.

AKA: 11D26;8D713. Date: 1958-61. Number: 212 . Thrust: 883.00 kN (198,506 lbf). Unfuelled mass: 760 kg (1,670 lb). Specific impulse: 293 s. Burn time: 125 s. Height: 2.03 m (6.66 ft). Diameter: 2.16 m (7.08 ft).

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.

Family: Storable liquid. Country: Russia. Launch Vehicles: R-16. Propellants: Nitric acid/UDMH. Stages: R-16-2. Agency: Glushko bureau. Bibliography: 225, 317, 320.

Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z