Thrust Chamber Design and Cooling
Student engineers working on this project are tasked with producing a preliminary design of the next generation liquid-fueled rocket engine for the UCI Rocket Project. The injector, combustion chamber, and nozzle are designed to achieve a given thrust and specific impulse while also being relatively simple to manufacture. Since these components are experiencing exceedingly high temperatures and heat fluxes, a suitable cooling system must be designed to maintain safe operating temperatures of the combustion chamber walls and nozzle.






















