Results from today's test fire of the new procedural rocket engine.
Configuration:
- Type: Liquid
- Power Cycle: Gas Generator
- Fuel: Kerolox
- Chamber Pressure: 10.0 MPa
- Nozzle Throat Radius: 0.1440 m
- Nozzle Exit Radius: 0.5400 m
- Nozzle Ratio: 14.06x
Performance:
- Total Thrust: 1,067 kN
- Isp (sea level): 298s
- Isp (vacuum): 324s
- Mass Flow: 364.79 kg/s
- Exit Mach Number: 3.59
- Exhaust Velocity: 3,071.80m/s