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BA-810
Beal H2O2/Kerosene rocket engine. Development 1990's. Pressure-fed engine with composite ablative chamber and nozzle. Helium pressurant. Thrust declines to 50% of initial value before shutdown.

Status: Development 1990's. Thrust: 3,600.00 kN (809,300 lbf). Specific impulse: 282 s. Burn time: 168 s.

Throttled thrust(vac): 1,800.000 kN (404,600 lbf). Area Ratio: 25.13. Oxidizer to Fuel Ratio: 7.5.

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