Gas turbine aircraft engines are among the most well-optimized systems in human industry. Despite this, their thermal efficiency falls well short of that of their ground-based counterparts, which use heavy co-generation systems that capture and reuse exhaust heat. Recent advancements in supercritical CO2 Brayton cycles and their proliferation into other industries promise extremely compact and power-dense means of capturing this heat and producing additional mechanical power. This paper presents a cycle topology novel to aerospace research and diagnoses a pinch point in the precooler as the main obstacle to previously considered systems. The partial heating cycle is shown to significantly outperform regenerated and unregenerated cycles, offering 26.6% more power per unit mass flow rate through the precooler.