Modeling Heat Flux Effects on Spacecraft at Atmospheric Re-entry

Spacecraft re-entry involves complex thermal and fluid dynamic interactions that critically impact vehicle design and survival. This research investigates heat flux dynamics during atmospheric transition, utilizing the Fay-Riddell equation to model heat transfer through spacecraft surfaces under varying conditions of altitude, Mach number, and nose radius. Key findings reveal that heat flux decreases exponentially with altitude, increases with velocity, and varies significantly with geometric configuration. The analysis demonstrates heat flux ranges from 3.21 × 10^4 W/m^2 with a 3m nose radius at Mach 10 and 30km altitude to 8.32 × 10^6 W/m^2 with a 0.1m nose radius at ground level, providing crucial insights for thermal protection system design. By quantifying these dynamic fluid properties, the research advances understanding of spacecraft thermal management, supporting more efficient and safer space travel technologies. The results derived offer a foundational approach to predicting and mitigating thermal risks in aerospace engineering, with potential applications in developing next-generation reusable rocket systems.