Pressure farfield
 

Hi guys,
I'm running supersonic flow simulation is fluent.
I'm using pressure far field boundary condition for inlet
where I'm providing the details of

• Static Pressure
• Mach Number
• Temperature

In my problem statement stagnation pressure is mentioned ... so i have to convert it into static pressure by using the below formula

P_stagn = P_static (1+(gamma-1)/2 X Mach Number^2 )^(gamma/(gamma-1))

P_stagn= 296000 Pa
Mach number = 2.18
gamma = 1.4

I calculated static pressure by using the above values and then the static pressure is 28562.51569 Pa


Am I in the right way in calculations?

I got the doubt because my solution is not getting appropriate results, I thought it might be issue with calculation..

Pls help me

Given those values your static pressure is correct.

Thank you.. what could be the solution

The solution for what? You haven't really provided enough information for anyone to understand your problem.

I'm getting divergence in the solution
Mesh statistics:
Orthogonal quality : 0.99652 (avg )
Skewness : 4.548e-2

Hello RaviTeja,

Are you running your simulation in single or double precision? Also, what is the timestep you are using for your simulation?