A　high　speed　compressible　gas　was　introduced　tangentially　into　an　adiabatic　convergent-divergent　nozzle,　thus　a　highly　swirling　supersonic　compressible　flow　was　formed.　Numerical　simulations　were　carried　out　of　the　flow　situations　with　various　inlet　swirling　intensity.　Both　temperature　and　velocity　distributions　inside　the　nozzle　are　obtained.　The　average　centrifugal　acceleration　at　the　nozzle　outlet　is　computed　and　its　relation　with　the　inlet　centrifugal　acceleration　was　analysed.　It　was　found　that　although　shock　wave　may　well　exist　at　the　nozzle　throat,　the　swirling　intensity　or　vorticity　can　still　be　enlarged　by　a　factor　of　2　to　10　at　the　nozzle　outlet.