Abstract
A numerical simulation is conducted to clarify the mechanism of total temperature separation in the vortex tube. The supersonic jet flow simulation is performed to validate the numerical simulation code. The flow structure and the acoustic characteristics of the oscillation modes for supersonic jet are in good agreement with past experimental resuts. Multiple computational domains are created for complicated geometries of the vortex tube, and the flow field is solved using the zonal mehod. The flow structure in the vortex tube can be successfully captured in this simulation. The existence of the acoustic streaming was clarified and the temperature difference caused by the total temperature separation in qualitatively good agreement with that of the experiment.
