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RD-214

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-214 Part of RD-107 RD-214 Credit: © Mark Wade Glushko Nitric acid/Kerosene rocket engine. R-12, Kosmos 11K63 stage 1. Single turbopump driven by H2O2 gas generator feeding four fixed chambers. Ignition with propellant TG-02. First flight 1957. Date: 1955-59. Number: 181 . Thrust: 730.00 kN (164,110 lbf). Unfuelled mass: 655 kg (1,444 lb). Specific impulse: 264 s. Specific impulse sea level: 230 s. Burn time: 140 s. Height: 1.48 m (4.85 ft). Diameter: 2.38 m (7.80 ft). Chamber Internal Diameter . 480 mm, throat diameter 176 mm. Diameter is per chamber. Chambers: 4. Thrust (sl): 635.200 kN (142,799 lbf). Thrust (sl): 64,752 kgf. Engine: 655 kg (1,444 lb). Chamber Pressure: 43.60 bar. Area Ratio: 9.42. Propellant Formulation: AK27I/TM-185. Thrust to Weight Ratio: 161.25. Oxidizer to Fuel Ratio: 3.97. Coefficient of Thrust vacuum: .67. Coefficient of Thrust sea level: .58. Family: Storable liquid. Country: Russia. Engines: RD-214. Launch Vehicles: R-12, R-12U, Kosmos 63S1, Kosmos 11K63, Kosmos 63S1M. Propellants: Nitric acid/Kerosene. Stages: Kosmos A-1. Agency: Glushko bureau. Bibliography: 225, 317, 320, 7510. Photo Gallery RD-214 Credit: © Mark Wade 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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