NK-39
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Kuznetsov LOx/Kerosene rocket engine. N-1F stage 3 (Block V). Development ended 1971. Modified version of original engine with multiple ignition capability. Never flown and mothballed after the cancellation of the N1.
After initial failures of the N-1 Kuznetsov developed modified versions of engines for all 3 stages, with multiple ignition capability and increased operational lifetime. These engines were never flown and were mothballed after the cancellation of the N1.
Engine: 631 kg (1,391 lb). Chamber Pressure: 98.00 bar. Area Ratio: 114. Thrust to Weight Ratio: 64.97. Oxidizer to Fuel Ratio: 2.6.
Related
- Country
- Russia
- Propellants
- Lox/Kerosene
- Stages
- N1F Block V
- Agency
- Kuznetsov bureau
- Bibliography
- 351