RD-108 home
topic index
R-7 aft end
Credit - © Mark Wade
Engine Model: RD-108-11D512. Manufacturer Name: RD-108. Government Designation: 11D512. Designer: Glushko. Application: Soyuz 11A511-1, Soyuz 11A511U-1. Propellants: Lox/Kerosene. Thrust(vac): 997.000 kN (224,134 lbf). Thrust(sl): 746.400 kN (167,797 lbf). Isp: 315 sec. Isp (sea level): 248 sec. Burn time: 286 sec. Mass Engine: 1,400 kg (3,000 lb). Diameter: 0.67 m (2.19 ft). Length: 2.86 m (9.38 ft). Chambers: 4. Chamber Pressure: 51.00 bar. Thrust to Weight Ratio: 72.59. Country: Russia. Status: Design 2000. First Flight: 1965. Last Flight: 2006. Flown: 752.

Diameter is per chamber.

Engine Model: RD-108-11D512P. Manufacturer Name: RD-108. Government Designation: 11D512P. Designer: Glushko. Application: Soyuz 11A511U2-1. Propellants: Lox/Kerosene. Thrust(vac): 1,011.000 kN (227,281 lbf). Thrust(sl): 788.400 kN (177,239 lbf). Isp: 319 sec. Isp (sea level): 252 sec. Burn time: 290 sec. Chambers: 4. Country: Russia. Status: Out of production. First Flight: 1982. Last Flight: 1995. Flown: 92.

A 1-2 second specific impulse increase was made possible by the use of synthetic fuel Sintin and a modified mixing head. This was a very complicated modification. Diameter is per chamber.

Engine Model: RD-108-8D727. Manufacturer Name: RD-108. Government Designation: 8D727. Other Designations: 8D727K, 8D727P. Designer: Glushko. Application: Molniya 1, Molniya 8K78M-1. Propellants: Lox/Kerosene. Thrust(vac): 977.000 kN (219,638 lbf). Isp: 316 sec. Isp (sea level): 251 sec. Burn time: 290 sec. Mass Engine: 1,230 kg (2,710 lb). Diameter: 0.75 m (2.45 ft). Length: 2.86 m (9.38 ft). Chambers: 4. Chamber Pressure: 53.60 bar. Oxidizer to Fuel Ratio: 2.39. Thrust to Weight Ratio: 80.97. Country: Russia. First Flight: 1964. Last Flight: 2006. Flown: 294.

OKB Glushko. Used on Molniya 8K78L, 8K78M and 11A57 Stage 1. Propellants kerosene (RG-1 or T-1) / Lox. Diameter is per chamber.

Engine Model: RD-108-8D727K. Manufacturer Name: RD-108. Government Designation: 8D727K. Designer: Glushko. Developed in: -1962. Application: Molniya 8K78-3. Propellants: Lox/Kerosene. Thrust(vac): 976.000 kN (219,413 lbf). Isp: 316 sec. Chambers: 4. Country: Russia. Status: Out of Production.

Engine Model: RD-108-8D75. Manufacturer Name: RD-108. Government Designation: 8D75. Designer: Glushko. Application: R-7 8K71-1, Vostok 8K72-1, Vostok 8K72K-1. Propellants: Lox/Kerosene. Thrust(vac): 912.000 kN (205,025 lbf). Thrust(sl): 713.600 kN (160,424 lbf). Isp: 308 sec. Isp (sea level): 241 sec. Burn time: 340 sec. Mass Engine: 1,278 kg (2,817 lb). Diameter: 0.67 m (2.19 ft). Length: 2.86 m (9.38 ft). Chambers: 4. Chamber Pressure: 51.00 bar. Area Ratio: 18.90. Oxidizer to Fuel Ratio: 2.39. Thrust to Weight Ratio: 72.76. Country: Russia. First Flight: 1957. Last Flight: 1961. Flown: 35.

OKB Glushko. Used on 8K71 R-7 Stage 1. Developed in 1954-1955. Propellants kerosene (RG-1) / Lox. Diameter is per chamber.

Engine Model: RD-108-8D75-1958. Manufacturer Name: RD-108. Government Designation: 8D75-1958. Designer: Glushko. Application: Luna 8K72-1. Propellants: Lox/Kerosene. Thrust(vac): 941.000 kN (211,545 lbf). Thrust(sl): 731.200 kN (164,380 lbf). Isp: 315 sec. Isp (sea level): 246 sec. Burn time: 340 sec. Mass Engine: 1,250 kg (2,750 lb). Diameter: 0.67 m (2.19 ft). Length: 2.86 m (9.38 ft). Chambers: 4. Chamber Pressure: 51.00 bar. Area Ratio: 18.90. Oxidizer to Fuel Ratio: 2.39. Thrust to Weight Ratio: 76.40. Country: Russia. Status: Out of production. First Flight: 1958. Last Flight: 1960. Flown: 9.00.

Diameter is per chamber.

Engine Model: RD-108-8D75-1959. Manufacturer Name: RD-108. Government Designation: 8D75-1959. Designer: Glushko. Propellants: Lox/Kerosene. Thrust(vac): 941.000 kN (211,545 lbf). Isp: 315 sec. Isp (sea level): 248 sec. Burn time: 340 sec. Mass Engine: 1,250 kg (2,750 lb). Diameter: 0.67 m (2.19 ft). Length: 2.86 m (9.38 ft). Chambers: 4. Chamber Pressure: 51.00 bar. Area Ratio: 18.90. Oxidizer to Fuel Ratio: 2.39. Thrust to Weight Ratio: 76.80. Country: Russia. Status: Out of production. First Flight: 1960. Last Flight: 1964. Flown: 13.

Further development of 8D74-1958, 1958-1959. Diameter is per chamber.

Engine Model: RD-108-8D75K. Manufacturer Name: RD-108. Government Designation: 8D75K. Designer: Glushko. Application: Molniya 8K78-1, R-7A 8K74-1, Voskhod 11A57-1, Vostok 8A92-1, Vostok 8A92M-1. Propellants: Lox/Kerosene. Thrust(vac): 941.000 kN (211,545 lbf). Thrust(sl): 740.400 kN (166,449 lbf). Isp: 315 sec. Isp (sea level): 248 sec. Burn time: 340 sec. Mass Engine: 1,252 kg (2,760 lb). Diameter: 0.67 m (2.19 ft). Length: 2.86 m (9.38 ft). Chambers: 4. Chamber Pressure: 51.00 bar. Area Ratio: 18.90. Thrust to Weight Ratio: 76.59. Country: Russia. First Flight: 1959. Last Flight: 1991. Flown: 488.

Diameter is per chamber.

Engine Model: RD-108-8D75PS. Manufacturer Name: RD-108. Government Designation: 8D75PS. Designer: Glushko. Application: Sputnik 8K71PS-1. Propellants: Lox/Kerosene. Thrust(vac): 912.000 kN (205,025 lbf). Thrust(sl): 713.600 kN (160,424 lbf). Isp: 308 sec. Isp (sea level): 241 sec. Burn time: 340 sec. Mass Engine: 1,250 kg (2,750 lb). Diameter: 0.67 m (2.19 ft). Length: 2.86 m (9.38 ft). Chambers: 4. Chamber Pressure: 53.00 bar. Area Ratio: 18.90. Thrust to Weight Ratio: 74.40. Country: Russia. Status: Out of Production. First Flight: 1957. Last Flight: 1958. Flown: 32.

Diameter is per chamber.

Engine Model: RD-108-8D77. Manufacturer Name: RD-108. Government Designation: 8D77. Designer: Glushko. Application: Sputnik 8A91-1. Propellants: Lox/Kerosene. Thrust(vac): 804.000 kN (180,746 lbf). Thrust(sl): 628.000 kN (141,180 lbf). Isp: 315 sec. Isp (sea level): 246 sec. Burn time: 370 sec. Mass Engine: 1,250 kg (2,750 lb). Diameter: 0.67 m (2.19 ft). Length: 2.86 m (9.38 ft). Chambers: 4. Chamber Pressure: 39.20 bar. Area Ratio: 18.90. Thrust to Weight Ratio: 65.60. Country: Russia. Status: Out of Production. First Flight: 1958. Last Flight: 1958. Flown: 2.00.

Diameter is per chamber.

RD-108 used on Rocket Stages
Contact us with any corrections, additions, or comments.
Conditions for use of drawings, pictures, or other materials from this site..
To contact astronauts or cosmonauts.

© Mark Wade, 1997 - 2008 except where otherwise noted.