A new approximate method to determine the aerodynamic coefficient and the convective heat transfer coefficient is presented. A simplified mathematical model is constructed of heat exchange processes in a laminar and turbulent boundary layer, which appears near the surface of an aircraft moving with hypersonic velocity. This mathematical model makes possible the calculation of the enhanced heat and mass transfer on the surface of a hypersonic aircraft of a complex geometric shape, including at low temperatures.
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Kuzenov et al. (2018) studied this question.