Supercritical carbon dioxide Brayton cycles offer high power densities, and limited research within aerospace propulsion has indicated they can reduce fuel burn by recovering exhaust heat from turbofan engines. Recent research in terrestrial applications has shown that the cycle topologies considered in propulsion research are sub-optimal for gas turbine bottoming cycles, suggesting a partial heating cycle offers the potential to recover more exhaust heat. Existing propulsion research fails to diagnose a pinch point in the pre-cooler heat exchanger, leading to a larger heat exchanger than is necessary and limiting total power output. This research adapts lessons from terrestrial research and considers novel means of mitigating this pinch point. © 2025, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.