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RD-212

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-212 Part of RD-107 Glushko Nitric acid/Kerosene rocket engine. Developed 1952-56. Original four-chamber engine design planned for the booster stage of the Buran intercontinental ramjet missile. Abandoned due to limited thrust; RD-213 was developed instead. Status: Developed 1952-56. Date: 1952-56. Thrust: 623.00 kN (140,055 lbf). Unfuelled mass: 642 kg (1,415 lb). Specific impulse: 253 s. Specific impulse sea level: 227 s. Burn time: 100 s. Height: 2.50 m (8.20 ft). Diameter: 1.48 m (4.85 ft). Development to 1957. Two thrust levels. Ignition with propellant TG-02. Chamber pressure 28,4 / 39,2 bar. Chambers: 4. Throttled thrust(vac): 437.000 kN (98,241 lbf). Engine: 642 kg (1,415 lb). Chamber Pressure: 39.20 bar. Area Ratio: 7.2. Propellant Formulation: AK27I/TM-185. Thrust to Weight Ratio: 98.9. Oxidizer to Fuel Ratio: 3.97. Family: Storable liquid. Country: Russia. Propellants: Nitric acid/Kerosene. Agency: Glushko bureau. Bibliography: 320, 344, 7508. Back to top of page 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 © 1997-2019 Mark Wade - Contact © / Conditions for Use

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