[bharath]

Hi to all,

I am simulating a de laval supersonic nozzle simulation.
Material as Steam using IAPWS table (CFX).Turbulence model as SST.

Nozzle parameters are Nozzle Pressure ratio = 0.201,Throat to exit area ratio = 1.3687,Gama =1.321

Target Mach number at nozzle exit is 1.7 usingIsentropic flow relations.
But i am getting exit mach number from CFX output 1.58.

I did Mesh sensitivity studies (3Million nodes to 12Million nodes).But nothing helps me to reach the targetted Mach number of 1.7

Could anybody tell me some advice on this.Thanks in advance