[ANUPAMA P A]

Hello all, I am facing an issue while analyzing compressible flow in a rocket nozzle. I have designed the nozzle using MOC with isentropic equations such that it achieves the ideal expansion at sea level condition. The chamber pressure and camber temperature calculated were 3.72MPa and 1120 K respectively. I used Ansys fluent for the analysis. I employed k-omega SST turbulence model for the analysis with density based solver since i am studying the nozzle at supersonic speeds. Air was used as the working fluid with ideal gas properties and viscosity was fixed as Sutherland in the software. The inlet was considered as pressure inlet as well mass flow inlet. All the spatial discretization was set to second order upwind. The coherent number was set as 5 with default control values. The residual of absolute criteria was set as 1e-03. An error occurs " The temperature is limited to cells at last 11 iterations". The operating pressure was set to 0. I have tried changing mesh quality and tried with different boundary conditions but the results were similar to the previous one causing the same error (diverged as well). Can anyone help me identify the*problem*please. I have also attached a pdf document with the following images.