Engine Performance
| |
NK-31 |
NK-39 |
Propellant Combination:
Oxidizer
Fuel |
Liquid Oxygen (LOX)
Rocket Propellant (RP) |
Liquid Oxygen (LOX)
Rocket Propellant (RP) |
| Average Thrust: |
90,500 lb
401,820 N |
90,500 lb
401,820 N |
| Chamber Pressure: (Pc) |
1,333 psia |
1,333 psia |
| Mixture Ratio: |
2.6 : 1 |
2.6 : 1 |
| Isp: |
353 sec |
352.5 sec |
| Nozzle Area Ratio: |
124 : 1 |
124 : 1 |
| Gimbal Capability: |
2.5 degrees |
0 degrees |
| Engine Mass: |
1,590 lb
722 kg |
1,287 lb
585 kg |
| Engine Thrust to Weight: |
57 |
70 |
| Mixture Ratio Control: |
Yes (EMA) |
Yes (EMA) |
| Throttle Range: (% Pc) |
55 - 100 % |
55 - 100 % |
| Restart Capability: |
Yes |
No |
Engine Size:
Length / Diameter |
10.3 / 5.9 ft
3.1 / 1.8 m |
10.0 / 5.9 ft
3.0 / 1.8 m |
| Flight Status: |
Flight Qualified |
Flight Qualified |
| Launch Vehicle: |
Russian N-1 4th Stage (Block G) |
Russian N-1 3rd Stage |
| Configuration: |
|
* Performance provided by GenCorp
Aerojet. The engine performance statistics listed on
this page are representative numbers only. Aerojet can not vouch for the complete
accuracy of the data.
|
