Abstract: This paper analyzes the heat transfer characteristics of high-Mach-number aircraft engine nacelle components in extreme high-temperature environments. Considering the rapid calculation requirements for component testing and thermal management design, a composite heat transfer network model was developed, primarily based on a full-order radiation heat transfer model and incorporating reduced-order convection and conduction heat transfer models. This model forms a hybrid reduced-order solution method, where radiation is treated in three dimensions, flow in one dimension, and convection heat transfer is modeled using empirical models. The algorithm enables fast calculation of relatively small temperature increases in nacelle components within large-scale structures, establishing a foundation for improving the iterative speed of nacelle thermal management design.