This is a supercut of the tests I've been conducting with my rocket engine.

I made this rocket engine for an engineering class during the fall semester, and this semester I've been working on improving the design as part of an independent study sponsored by my engineering professor. I've had a blast (literally!) working on this project, and I've learned so much from it.

The engine burns a 1/1.5 ratio of ethanol/gaseous-oxygen, at a chamber pressure of 150psi. For more information on the design and development, visit this link: [ Ссылка ]

The expected thrust based off my design calculations was 81N. The nozzle section had been over-expanded in the first three tests, and so once that issue was resolved it was able to achieve 96% of the calculated thrust output. I was able to gather thrust data for the last four tests, and the peak thrust output from each test were:
FEB 10: 45N
FEB 13: 64N
FEB 20: 66N
MAR 8: 78N

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