RD-214
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Credit: © Mark Wade
Glushko Nitric acid/Kerosene rocket engine. R-12, Kosmos 11K63 stage 1. Single turbopump driven by H2O2 gas generator feeding four fixed chambers. Ignition with propellant TG-02. First flight 1957.
Chamber Internal Diameter . 480 mm, throat diameter 176 mm. Diameter is per chamber.
Chambers: 4. Thrust (sl): 635.200 kN (142,799 lbf). Thrust (sl): 64,752 kgf. Engine: 655 kg (1,444 lb). Chamber Pressure: 43.60 bar. Area Ratio: 9.42. Propellant Formulation: AK27I/TM-185. Thrust to Weight Ratio: 161.25. Oxidizer to Fuel Ratio: 3.97. Coefficient of Thrust vacuum: .67. Coefficient of Thrust sea level: .58.
Related
- Family
- Storable liquid
- Country
- Russia
- Engines
- RD-214
- Launch Vehicles
- R-12, R-12U, Kosmos 63S1, Kosmos 11K63, Kosmos 63S1M
- Propellants
- Nitric acid/Kerosene
- Stages
- Kosmos A-1
- Agency
- Glushko bureau
Photo Gallery
RD-214
Credit: © Mark Wade
