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Engine Model: Plug-Nozzle Pegasus. Propellants: Lox/LH2. Thrust(vac): 23,928.000 kN (5,379,228 lbf). Thrust(sl): 18,714.800 kN (4,207,254 lbf). Isp: 459 sec. Isp (sea level): 359 sec. Burn time: 232 sec. Chambers: 1. Country: USA. Status: Study 1966.
Plug-Nozzle Pegasus used on Rocket Stages
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© Mark Wade, 1997 - 2008 except where otherwise noted.
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