Glushko Lox/Alcohol rocket engine. 500.1 kN. R-5M 8K51. Isp=248s. First flight 1953.
Application: R-5M 8K51.
Thrust (sl): 432.000 kN (97,117 lbf). Thrust (sl): 44,052 kgf. Engine: 867 kg (1,911 lb). Chamber Pressure: 23.90 bar. Propellant Formulation: Lox/Alcohol-96%. Thrust to Weight Ratio: 58.82. Oxidizer to Fuel Ratio: 1.44.
More... - Chronology...
Unfuelled mass: 867 kg (1,911 lb).
Height: 3.22 m (10.57 ft).
Diameter: 1.65 m (5.41 ft).
Thrust: 500.10 kN (112,427 lbf).
Specific impulse: 248 s.
Specific impulse sea level: 220 s.
Burn time: 120 s.
First Launch: 1950-55.
Number: 134 .
Associated Launch Vehicles
R-5 Russian intermediate range ballistic missile. The R-5 was the first Soviet missile to be armed with a nuclear warhead, the first for which the new southern facility at Dnepropetrovsk took over full design and production responsibility. It was also the end of the road in being the ultimate extrapolation of German V-2 technology. Later missiles of both Yangel and Korolev would use other propellants and engine designs. More...
Associated Manufacturers and Agencies
Glushko Russian manufacturer of rocket engines and rockets. Glushko Design Bureau, Russia. More...
Lox/Alcohol Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. Alcohol (C2H5OH) was the fuel used for the German V-2 rocket, and the first derivative rocket engines in the United States, Soviet Union, and China used it as well. Better performance was achieved by increasing the alcohol concentration in the post-war engines. But after better-performance rocket-grade kerosene was developed by Rocketdyne in the REAP program of 1953, use of alcohol was abandoned. More...
R-5 Lox/Alcohol propellant rocket stage. Loaded/empty mass 27,250/3,250 kg. Thrust 479.22 kN. Vacuum specific impulse 244 seconds. More...
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