Аннотация:A new method for separating from the flow “cold” and “hot” parts which formed in the process of energy
separation in the boundary layer of a compressible gas is presented. For this purpose, a cylindrical channel
with permeable wall was used, which was connected to the settling chamber with compressed air through the
supersonic nozzle. With the release of air into the environment, some of the flow seeped through the
permeable wall, and its stagnation temperature was less than the initial one. The remaining part of the flow at
the tube’s outlet had a stagnation temperature greater than the initial one. The cooling effect was five times
greater than the Joule-Thomson effect for the investigated range of pressures and temperatures. Up to a
certain point, the increase in the initial pressure of the compressed air led to an increase in the temperature
difference between the cold and hot flows. But after that point the temperature difference remained almost
constant.