Beal H2O2/Kerosene rocket engine. Development 1990's. Pressure-fed restartable engine with composite ablative chamber and nozzle. Helium pressurant. Thrust declines to 50% of initial value before shutdown.
Status: Development 1990's. Thrust: 196.00 kN (44,062 lbf). Specific impulse: 300 s. Burn time: 600 s.
Throttled thrust(vac): 98.000 kN (22,031 lbf). Area Ratio: 100. Oxidizer to Fuel Ratio: 7.5. Restarts: 3.