Aerodynamic heating characteristics are fundamental to the design of thermal protection and management systems for high-speed aircraft. In this study, compressible numerical simulation and the floating heat-flux method were employed to calculate aerodynamic heating characteristics on the intake surface. Two key parameters, the recovery temperature and heat transfer coefficient, were used to characterize the aerodynamic thermal distribution of an aircraft. Parametric analyses were conducted for inlet Mach numbers ranging from 0.8 to 5 and flight altitudes from 11,000 to 36,000 m. Results indicate that the aerodynamic thermal effect is enhanced with increasing Mach number and flight altitude. Airflow pressure and heat flux at the intake surface are reduced by the expansion waves, whereas shock-wave compression and shock-induced boundary-layer separation are the primary contributors to localized high heat flux. Additionally, regions of higher pressure exhibit correspondingly higher heat flux.
Bao et al. (Sun,) studied this question.