This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
Designer: Beal. Used on stages: Beal BA-2 Stage 1. Propellants: H2O2/Kerosene Thrust(vac): 1,440,000 kgf. Thrust(vac): 14,100.00 kN. Isp: 259 sec. Burn time: 131 sec. Chambers: 1. Area Ratio: 6.48. Oxidizer to Fuel Ratio: 7.00. Country: USA. Status: Development. References: 455 . Comments: Pressure-fed engine with composite ablative chamber and nozzle. Helium pressurant. Thrust declines to 70% of initial value before shutdown.
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Last update 12 March 2001.
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© Mark Wade, 2001 .