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BA-3200
Beal H2O2/Kerosene rocket engine. Development 1990's. Pressure-fed engine with composite ablative chamber and nozzle. Helium pressurant. Thrust declines to 70% of initial value before shutdown.

Status: Development 1990's. Thrust: 14,100.00 kN (3,169,800 lbf). Specific impulse: 259 s. Burn time: 131 s.

Throttled thrust(vac): 9,870.000 kN (2,218,860 lbf). Area Ratio: 6.48. Oxidizer to Fuel Ratio: 7.

Family: Storable liquid. Country: USA. Propellants: H2O2/Kerosene. Stages: Beal BA-2 Stage 1. Agency: Beal. Bibliography: 455.
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