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RD-107-8D74K

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-107-8D74K Part of RD-107 RD-107 Credit: © Mark Wade Glushko LOx/Kerosene rocket engine. Developed in 1957-1960. Used in strap-ons for Molniya 8K78, R-7A 8K74, Voskhod 11A57, Vostok 8A92, Vostok 8A92M. Fuel T-1 or RG-1 kerosene. First flight 1959. AKA: 8D74K. Number: 1952 . Thrust: 996.00 kN (223,909 lbf). Unfuelled mass: 1,145 kg (2,524 lb). Specific impulse: 313 s. Specific impulse sea level: 256 s. Burn time: 119 s. Height: 2.86 m (9.38 ft). Diameter: 0.67 m (2.19 ft). Diameter is per chamber. Chambers: 4. Thrust (sl): 814.000 kN (182,994 lbf). Thrust (sl): 83,016 kgf. Engine: 1,145 kg (2,524 lb). Chamber Pressure: 59.70 bar. Area Ratio: 18.9. Thrust to Weight Ratio: 88.64. Country: Russia. Launch Vehicles: R-7A, Molniya 8K78, Voskhod 11A57, Vostok 8A92, Sputnik 11A59, Vostok 8A92M. Propellants: Lox/Kerosene. Stages: Molniya 8K78-0, R-7A 8K74-0, Vostok 8A92-0, Voskhod 11A57-0, Vostok 8A92M-0. Agency: Glushko bureau. Photo Gallery R-7 aft end 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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