ABOUT NK-33
The NK-33 is a closed-cycle oxygen-rich staged combustion engine originally designed by SNTK Kuznetsov for the Soviet N1 lunar rocket in the late 1960s. After the N1 program cancellation, stockpiled engines were preserved and later used on the Soyuz 2.1v and the American Antares rocket (as the AJ-26). The NK-33 was decades ahead of its time in performance and efficiency.
Image: Roscosmos
PERFORMANCE
| Thrust (Sea Level) | 1,510 kN (339,000 lbf) kN |
| Thrust (Vacuum) | 1,680 kN (378,000 lbf) kN |
| ISP (Sea Level) | 297 s s |
| ISP (Vacuum) | 331 s s |
| Chamber Pressure | 14.5 MPa (2,100 psi) bar |
| Mass | 1 kg |
| Thrust-to-Weight | 137 |
| Throttle Range | Not throttleable |
| Restart Capable | No |
THRUST CONVERSIONS (VACUUM)
| Kilonewtons | 1.0 kN |
| Pounds-force | 225 lbf |
ENGINE CYCLE
Oxygen-Rich Staged Combustion
PROPULSION
| Propellant | RP-1 |
| Oxidizer | LOX |
| Engine Cycle | Oxygen-Rich Staged Combustion |
| Mixture Ratio | 2.8:1 |
| Flow Rate | ~518 kg/s kg/s |
PHYSICAL
| Dimensions | 1.45 m diameter × 3.7 m length |
| Combustion Chambers | 1 |
| Nozzle Expansion Ratio | 26.8:1:1 |
GENERAL
| Manufacturer | SNTK Kuznetsov |
| Country | Russia / USSR |
| Status | Retired |
| First Flight | January 1, 1970 |
VARIANTS (3)
- NK-33
- NK-33-1
- AJ-26 (Aerojet adaptation)
VEHICLES USING NK-33 (3)
- N1 (Block A)
- Soyuz 2.1v
- Antares 100 series
ENGINE LINEAGE
NK-33→NK-33-1 (upgraded)
⚖ PROPELLANTS
