飞行器在高速飞行过程中，头部激波会强烈压缩来流使得气体温度急剧增大，激发高温非平衡效应。高温非平衡效应与湍流耦合作用形成高焓湍流边界层，使得飞行器表面热流生成机制变得更加复杂。基于内能守恒方程，推导出适用于高焓湍流边界层的热流分解公式，并对高焓零压力梯度平板湍流边界层热流生成机制进行分析，重点关注了黏性耗散作用对热流生成的影响。结果表明，黏性耗散是热流生成的主要来源，高温非平衡效应会在近壁区增大黏性耗散的贡献。黏性耗散作用可以分解为平均黏性耗散、脉动黏性耗散2部分，分别主要分布于近壁区和对数区。2部分黏性耗散作用都对壁面热流产生显著影响，且平均黏性耗散对壁面热流的贡献大约是脉动黏性耗散的2倍。

During the high-speed flight of the aircraft， the head shock wave will strongly compress the incoming flow， which will lead to a sharp increase in gas temperature and stimulate the high-temperature non-equilibrium effect. The high-enthalpy turbulent boundary layer is formed by coupling high temperature non-equilibrium effects and turbulence， which makes the formation mechanism of wall heat flux on the aircraft surface more complex. In this paper， based on the internal energy conservation equation， the heat flux decomposition formula suitable for the high-enthalpy turbulent boundary layer is derived. The heat flux generation mechanism of the high enthalpy zero-pressure gradient plate turbulent boundary layer is analyzed， focusing on the effect of viscous dissipation on the generation of wall heat flux. The results show that viscous dissipation is the main source of heat flux generation， and the high temperature non-equilibrium effect increases the contribution of viscous dissipation near the wall. The viscous dissipation can be divided into two parts： average and fluctuating ones， which are mainly distributed in the near-wall region and logarithmic region， respectively. The two parts of viscous dissipation have a significant effect on the wall heat flux， and the contribution of the average viscous dissipation on the wall heat flux is about twice that of the fluctuating viscous dissipation.