Experimental Design, Fabrication and Validation of a Liquid Rocket Engine

What is it about?

This paper describes how we designed, built, and tested a small-scale liquid rocket engine that produces about 1000 N of thrust. Using gaseous oxygen as the oxidizer and a blend of 70% ethanol with 30% water as fuel, we focused on creating a cost-effective engine using locally available materials and in-house manufacturing processes. We developed key components—including the combustion chamber, de Laval nozzle, and injector system—supported by detailed theoretical calculations and MATLAB simulations. After assembling the engine and its supporting test stand, we conducted several hot-fire tests, which demonstrated stable subsonic combustion despite minor challenges like less-than-ideal fuel atomization. Our results show that it’s feasible to build a functional liquid rocket engine on a limited budget, laying the groundwork for future improvements such as enhanced injector designs and better cooling methods.

Featured Image

Photo by SpaceX on Unsplash

Photo by SpaceX on Unsplash

Why is it important?

This research is important because it simplifies rocket engine development for student-level research, making complex propulsion technology more accessible. By designing a small-scale liquid bipropellant engine using cost-effective materials and innovative engineering approaches, we bridge the gap between academic learning and practical application. Our work provides a foundation for future student researchers to explore rocket science without the need for high-budget facilities, encouraging hands-on experimentation and innovation in aerospace engineering.