Procedural Rocket Engine Test Fire [Teaser]

Results from today's test fire of the new procedural rocket engine.

• 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
  

• 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