Plug-Nozzle Rombus

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Engine Model: Plug-Nozzle Rombus. Propellants: Lox/LH2. Thrust(vac): 101,988.000 kN (22,927,814 lbf). Thrust(sl): 79,768.100 kN (17,932,582 lbf). Isp: 459 sec. Isp (sea level): 359 sec. Burn time: 215 sec. Chambers: 1. Country: USA. Status: Study 1964. Plug-Nozzle Rombus used on Rocket Stages Used on stage: Rombus. on launch vehicle: Rombus. Contact us with any corrections, additions, or comments. Conditions for use of drawings, pictures, or other materials from this site.. To contact astronauts or cosmonauts. © Mark Wade, 1997 - 2008 except where otherwise noted.