RD-108-8D75-1959

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-108-8D75-1959

Part of RD-107

Glushko LOx/Kerosene rocket engine. Out of production. Further development of 8D74-1958, 1958-1959. Diameter is per chamber. Used on Vostok 8K72K launch vehicle. First flight 1960.

AKA: 8D75-1959. Status: Out of production. Number: 13 . Thrust: 941.00 kN (211,545 lbf). Unfuelled mass: 1,250 kg (2,750 lb). Specific impulse: 315 s. Specific impulse sea level: 248 s. Burn time: 340 s. Height: 2.86 m (9.38 ft). Diameter: 0.67 m (2.19 ft).

Chambers: 4. Engine: 1,250 kg (2,750 lb). Chamber Pressure: 51.00 bar. Area Ratio: 18.9. Thrust to Weight Ratio: 76.8. Oxidizer to Fuel Ratio: 2.39.

Country: Russia. Launch Vehicles: Vostok 8K72K. Propellants: Lox/Kerosene. Stages: Vostok 8K72K-1. Agency: Glushko bureau.

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