Launchers 3 D printed rocket engine ( E 1) 30s test at O, F ratio 2. 6

Successful 30second test at the stoichiometric oxidizer, fuel (OF) ratio of 2. 6 for LOX, RP1. Great throat, engine condition posttest, handling combustion temperature of about 6, 000 Degrees Fahrenheit (3, 315 Degrees Celsius). This is made possible due to our chamber regenerative cooling design as the melting point of the material of E1 s combustion chamber (Inconel 718) is 2, 500 F (1, 371 Degrees Celsius)