Determination of the heat transfer properties of a turbulent boundary layer in the case of supersonic flow when the temperature distribution along the constraining wall is arbitrarily assigned

Summary

In this investigation of the turbulent boundary layer in the compressible regime, the heat transfer is determined, at the wall, under the assumption that the temperature distribution along the wall is arbitrarily assigned, but with the proviso that there is not to be any pressure gradient present in the external potential flow. This objective is attained by making use of a method that may be considered to be an extension of the one employed previously by Lighthill [1] in his treatment of the analogous problem which arises in the laminar regime, and recourse is also had to an opportune hypothesis concerning the nature of the velocity distribution across the boundary layer in supersonic flow (which is substantiated by cited experimental results). In addition, the corresponding temperature distribution through the boundary layer is also adduced.

This work was carried out for the Cornell Aeronautical Laboratory, Inc., under sponsorship of the U.S. Navy Bureau of Ordnance, Section T Contract No. NOrd-14523, and coordinated by the Applied Physics Laboratory of the Johns Hopkins University.