  The generation mechanism of wall heat flux is one of the fundamental problems
in supersonic/hypersonic turbulent boundary layers. A novel heat decomposition
formula under the curvilinear coordinate was proposed in this paper. The new
formula has wider application scope and can be applied in the configurations
with grid deformed. The wall heat flux of an interaction between shock wave and
the turbulent boundary layer over a compression corner is analyzed by the new
formula. The results indicated good performance of the formula in the complex
interaction region. The contributions of different energy transport processes
were obtained. The contributions by the turbulent fluctuations e.g., Reynolds
stresses and turbulent transport of heat flux, were significantly increased,
while the processes by the mean profile e.g., molecular stresses and heat
conduction, can be neglected. In addition, the pressure work is another
contributor to the wall heat flux and the streamwise component works mainly in
the shear layer and the reattachment point, while pressure in the wall-normal
direction is concentrated in the vicinity of the reattachment point.
