Abstract
Understanding the generation mechanism of the heat flux is essential for the design of hypersonic vehicles. We proposed a novel formula to decompose the heat flux coefficient into the contributions of different terms by integrating the conservative equation of the total energy. The reliability of the formula is well demonstrated by the direct numerical simulation results of a hypersonic transitional boundary layer. Through this formula, the exact process of the energy transport in the boundary layer can be explained and the dominant contributors to the heat flux can be explored, which are beneficial for the prediction of the heat and design of the thermal protection devices.
Highlights
The heat transfer prediction is of great importance for hypersonic vehicles
The performance of the formula has been well demonstrated by DNS results of a hypersonic transitional boundary layer
It is found that the heat flux produced by the work done by Reynolds stresses and molecular stresses is much higher than the time-averaged heat flux on the wall
Summary
The heat transfer prediction is of great importance for hypersonic vehicles. When the transition or turbulence happens, the accurate prediction becomes even more challenging. Ebadi et al [8] obtained the wall heat flux by a triple integration of the Reynolds averaged energy equation for the two-dimensional incompressible turbulent boundary layer. Ghosh [11] proposed that the wall heat flux can be expressed by the sum of the integrations of different viscous terms in the incompressible turbulent channel and pipe flow.
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