Wall Heat Transfer Effects on Supersonic Nozzle Wall Boundary-Layer Temperature Profiles.

摘要

Measurements are reported of the total temperature profile in the turbulent boundary layer on a supersonic tunnel nozzle wall for two values of tunnel total temperature. The resulting two conditions of tunnel wall heat transfer history significantly affected the temperature profiles. The trend of the data is shown to agree with the wall heat transfer history when evaluated in terms of the enthalpy flux deficit. (Author)