On the Impact of Surface Thermal Conditions on Aero-heating to Hypersonic Vehicle

Document Type : Original Article

Authors

Aerospace Engineering Department, Military Technical College, Cairo, 11776, Egypt.

10.1088/1742-6596/3070/1/012006

Abstract

A numerical simulation tool is utilized to predict the heat flux distribution on the surface of a hypersonic vehicle flying at Mach 10. The study considers multiple factors influencing heat flux distribution, such as variations in isothermal wall temperature and nose radius. Additionally, it examines the adiabatic and adiabatic-radiation wall temperatures along the body surface. The model incorporates thermal non-equilibrium real gas properties and accounts for vibrational and electronic energy modes. Air is modeled as a mixture of five non-reacting species, with dynamic viscosity, specific heat, and thermal conductivity determined using non-equilibrium kinetic theory. This approach ensures accurate representation of the transport properties of gases in non-equilibrium states. The computational results are accurately validated against published experimental data to ensure the accuracy and reliability of the predictions.
International Conference on Aerospace Sciences and Aviation Technology
Volume 21, Issue 21
21st International Conference on Aerospace Sciences & Aviation Technology, ASAT 21, 2025.
September 2025
Pages 1-9

Files

Share

How to cite

Statistics