Abstract
An approximate theory of nonequilibrium stagnation point boundary layer flow on highly cooled blunt bodies at hypersonic flight speeds, including a finite atom recombination rate on the surface, is presented. The analysis is based on a simplified nonlinear representation of the reaction rate distribution across the boundary layer which is derived from the fact that recombination near the wall dominates the nonequilibrium behavior when the wall is highly cooled. Closed-form solutions for the conditions at the gas/solid interface, such as atom concentration at the wall and heat transfer, are obtained in terms of a universal function of a single, composite Damkohler number. This number represents the combined effects of homogeneous and heterogeneous reaction over a wide range of the various thermochemical parameters involved. The theory is found to be in good agreement with the numerical results for nonequilibrium flow reported by Fay and Riddell.
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