RD-101

Glushko LOx/Alcohol rocket engine. R-2 and V-2A. Developed simultaneously with the RD-100 but with no German involvement. More compact, increased thrust, increased chamber pressure and higher alcohol concentration. First flight 1949.

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!

Thrust (sl): 363.000 kN (81,605 lbf). Thrust (sl): 37,016 kgf. Engine: 888 kg (1,957 lb). Chamber Pressure: 21.20 bar. Propellant Formulation: Lox/Alcohol-96%. Thrust to Weight Ratio: 48.8636363636364. Oxidizer to Fuel Ratio: 1.45.