Engine Performance

	NK-33 (AJ26-58,59)	NK-43 (AJ26-60)
Propellant Combination      Oxidizer      Fuel	Liquid Oxygen (LOX) Rocket Propellant (RP)	Liquid Oxygen (LOX) Rocket Propellant (RP)
Average Thrust:	339,000 lbf SL 1,505 kN SL	395,000 lbf 1,753.8 kN
Chamber Pressure: (Pc)	2109 psia 145 bar	2109 psia 145 bar
Mixture Ratio:	2.6 : 1	2.6 : 1
Isp:	297 sec SL 331 sec vac	346 sec
Nozzle Area Ratio:	27 : 1	80 : 1
Gimbal Capability:	6 degrees (w/ Aerojet modification)	6 degrees (w/ Aerojet modification)
Engine Mass:	2,725 lb 1,235 kg	3,250 lb 1,473 kg
Engine Thrust to Weight	125	121
Mixture Ratio Control:	Yes (EMA)	Yes (EMA)
Throttle Range: (% Pc)	55 - 104 %	55 - 104 %
Restart Capability:	AJ26-58:  No AJ26-59:  Yes	AJ26-60:  No
Engine Size:      Length / Diameter	12.2  /  6.7  ft 3.7  /  2.0  m	16.3  /  8.2  ft 5.0  /  2.5  m
Flight Status	Flight Qualified	Flight Qualified
Launch Vehicles:	Russian N-1 First Stage (30 engines) Development - K-1 First Stage (3 engines)	Russian N-1 Second Stage (8 engines) Development - K-1 Second Stage (1 engine)
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.