Plug-Nozzle Pegasus
Engine · USA
Original archive entry. The text, images and links below are kept as they were written.
Notional LOx/LH2 rocket engine. Study 1966. Used on Pegasus VTOVL launch vehicle.
Thrust (sl): 18,714.800 kN (4,207,254 lbf). Thrust (sl): 1,908,410 kgf.
Related
- Country
- USA
- Launch Vehicles
- Pegasus VTOVL
- Propellants
- Lox/LH2
- Stages
- Pegasus VTOVL stage