This research explores how Triply-Periodic Minimal Surface (TPMS) structures can improve transpiration cooling by optimizing coolant flow and reducing pressure losses in aerospace applications. Transpiration cooling relies on porous materials to evenly distribute coolant and protect critical components from extreme heat, but the complex geometries of TPMS structures present challenges in understanding their flow resistance and permeability. Currently, there is limited data on how different TPMS designs influence pressure drop and fluid behavior, making it difficult to implement these structures effectively. To address this, the study will use Computational Fluid Dynamics (CFD) simulations and experimental tests to analyze how different TPMS unit cell sizes and geometries affect pressure drop, coolant distribution, and flow efficiency. Simulations will be performed under realistic aerospace operating conditions, and results will be compared to experimental data to ensure accuracy. The goal of this research is to provide design guidelines for optimizing TPMS structures in transpiration cooling for applications involving hypersonic vehicles and gas turbine engines. By improving our understanding of how fluid moves through these porous materials, this study will help develop more efficient cooling systems for gas turbines, hypersonic vehicles, and other high-temperature aerospace applications, contributing to advancements in next-generation thermal management technologies.