Skin-friction and heat-transfer decompositions in hypersonic transitional and turbulent boundary layers

The decompositions of the skin-friction and heat transfer coefficients based on two-fold repeated integration in hypersonic transitional turbulent boundary layers are analyzed to explain generations wall skin friction transfer. Reynolds analogy factor slightly increases as temperature decreases, especially for extremely cooled wall. integral analysis is applied overshoot behaviours layers. coefficient mainly caused by drastic change mean velocity profiles, primarily due viscous dissipation. In layers, increase significantly decreases. effects gradients shear stress contribute dominantly friction, have weak correlations with temperature, except strongly condition. condition high Mach number can enhance effect stress, weaken impact gradients. Furthermore, magnitudes dominant relative contributions gradients, pressure dilatation, dissipation flux