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

TL;DR

This paper analyzes the generation of skin friction and heat transfer in hypersonic boundary layers, revealing how wall temperature and flow conditions influence these coefficients and their overshoot behaviors.

Contribution

It provides a detailed integral analysis of skin friction and heat transfer mechanisms in hypersonic transitional and turbulent boundary layers, highlighting effects of wall temperature and flow parameters.

Findings

Overshoot of skin friction caused by velocity profile changes

Heat transfer overshoot primarily due to viscous dissipation

Wall temperature significantly affects skin friction and heat transfer coefficients

Abstract

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