Back to the Purdue AAE Propulsion main page. Back to the Liquid Rockets page.



Engine statistics
Specification Two chambers
Applications Titan launch vehicle family
Propellants LOX/RP-1 or storables, ground tested with LOX/LH2
Thrust in Vacuum 276,300 x 2 = 552,600 lb
Thrust at Sea Level ????
Isp in vacuum(s) 304
Isp at sea level ????
Mixture Ratio 1.91:1
Weight 4780 lb
Chamber Pressure 860 psia
Expansion Ratio 16.7:1
Engine Cycle ????
Pump Design Pressures ????