Hi,

I'm not able to start a supersonic-Calculation in FLUENT. Here the facts. Please check it! If there are any problems, please note me.

thanks a lot!!!

pressure_inlet: Gauge Total Pressure = 300000 Pa

Initial Gauge Pressure = 0 Pa

pressure_outlet: Gauge Pressure = 0 Pa

Solver: Standard k-Omega-Model

Steady

Coupled

Material: air - ideal gas

cp = constant

Therm. Cond. = constant

Viscosity = sutherland

thanks for your efforts

Hi u put the static pressure in the place of Initial Gauge Pressure . For e.g For M2 For Po=295760 Pstatic is 37800 Pa.

Regards Prasatth

Thanks Prasath,

How I can calculate the pressures at M = 2 ?