Engine Model: Chamber/single nozzle. Propellants: Lox/LH2. Thrust(vac): 13,231.000 kN (2,974,447 lbf). Isp: 455 sec. Isp (sea level): 365 sec. Burn time: 249 sec. Chambers: 1. Country: USA. Status: Study 1963. Before moving to favored plug nozzle designs, Bono at Douglas considered having multiple combustion chambers exhaust into a single large nozzle to obtained Improved Specific Impulse. Used in Nova DAC ISI, ROOS ISI, OOST ISI, and DAC Helios ISI designs. Status: Study 1963. Operational date would have been July 1977. Values shown were maximum considered.
Chamber/single nozzle used on Rocket Stages
- Used on stage: OOST. on launch vehicle: OOST.