Launcher’s 3D printed rocket engine (E-1) - 30s test at O/F ratio 2.6

Successful 30-second test at the stoichiometric oxidizer/fuel (OF) ratio of 2.6 for LOX/RP-1. Great throat/engine condition post-test, 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 E-1’s combustion chamber (Inconel 718) is 2,500 F (1,371 Degrees Celsius)