Fuel-Bound Oxygen Penalty and System-Level Screening of Oxygenated Fuels for LOX Rocket Propulsion: A NASA CEA Thermochemical Assessment

This research project presents a comprehensive thermochemical evaluation and system-level screening of oxygenated alternative fuels compared to conventional RP-1 in liquid oxygen (LOX) rocket propulsion systems. Utilizing the NASA Chemical Equilibrium with Applications (CEA) program, the study systematically analyzes the performance penalties associated with fuel-bound oxygen across various candidates, including dimethyl ether, ethanol, methanol, acetic acid, and formic acid. The evaluation methodology involves extensive oxidizer-to-fuel ratio sweeps, chamber pressure sensitivity analyses, and nozzle expansion ratio variations under both equilibrium and frozen flow assumptions. Key performance metrics such as equivalent exhaust velocity, density impulse, thermal severity, and total propellant volume requirements are quantified. The simulation framework provides structured guidance for assessing

how molecularly bound oxygen influences combustion temperature, exhaust species distribution, and overall propulsion efficiency. This research direction offers a valuable methodology for early-stage propellant screening, highlighting the trade-offs between environmental benefits, storage requirements, and thermodynamic performance retention in next-generation rocket engines. By analyzing these boundary cases, the project establishes a robust analytical model to support the design and optimization of alternative-fuel rocket propulsion systems.

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