Condensation in a contoured-nozzle shock tunnel

Abstract : The onset of condensation in a hypersonic shock tunnel was investigated to determine the limiting temperature to which the gas may be expanded. Previous research indicated some supercooling could be obtained; however, a confident assessment could not be made because of scatter in available experimental results. Static wall pressure and pitot pressure, which vary with condensation, were measured, while reservoir temperature was reduced for constant reservoir pressure. Under these conditions, measurements were made of condensation and supercooling. (Author)