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Plug-Nozzle Pegasus
Notional LOx/LH2 rocket engine. Study 1966. Used on Pegasus VTOVL launch vehicle.

Status: Study 1966. Thrust: 23,928.00 kN (5,379,228 lbf). Specific impulse: 459 s. Specific impulse sea level: 359 s. Burn time: 232 s.

Thrust (sl): 18,714.800 kN (4,207,254 lbf). Thrust (sl): 1,908,410 kgf.



Country: USA. Launch Vehicles: Pegasus VTOVL. Propellants: Lox/LH2. Stages: Pegasus VTOVL stage.

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