This page no longer updated from 31 October 2001. Latest version can be found at RD-101

Manufacturer Name: RD-101. Designer: Glushko. Developed in: 1946-51. Application: R-2 and V-2A. Used on stages: R-2. Used on launch vehicles: R-2. Propellants: Lox/Alcohol Thrust(vac): 41,200 kgf. Thrust(vac): 404.00 kN. Isp: 237 sec. Isp (sea level): 210 sec. Mass Engine: 888 kg. Diameter: 1.6 m. Length: 3.4 m. Chambers: 1. Chamber Pressure: 21.20 bar. Oxidizer to Fuel Ratio: 1.45. Thrust to Weight Ratio: 48.86. Country: Russia. Status: Out of Production. First Flight: 1966. Last Flight: 1966. Flown: 1. References: 287 , 317 , 342 .

The RD-101 was developed simultaneously with the RD-100 but with no German involvement (for security). It was more compact, had increased thrust (37,000 kgf), increased pressure and an increased alcohol concentration. They were nicknamed drunk engines and test specialists used to get the alcohol out afterwards for their own uses!

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Last update 12 March 2001.
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