Pressure farfield

raviteja gonnabathula · July 2, 2020, 08:06

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

agd · July 2, 2020, 10:52

Given those values your static pressure is correct.

raviteja gonnabathula · July 2, 2020, 12:30

Thank you.. what could be the solution

agd · July 2, 2020, 12:49

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

raviteja gonnabathula · July 2, 2020, 23:54

Quote:

Originally Posted by agd

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

aero_head · November 14, 2020, 17:31

Hello RaviTeja,

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

July 2, 2020, 08:06	Pressure farfield	#1
raviteja gonnabathula New Member RaviTeja Gonnabathula Join Date: Oct 2019 Posts: 10 Rep Power: 6	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

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July 2, 2020, 10:52		#2
agd Senior Member Join Date: Jul 2009 Posts: 351 Rep Power: 18	Given those values your static pressure is correct.

July 2, 2020, 12:30		#3
raviteja gonnabathula New Member RaviTeja Gonnabathula Join Date: Oct 2019 Posts: 10 Rep Power: 6	Thank you.. what could be the solution

July 2, 2020, 12:49		#4
agd Senior Member Join Date: Jul 2009 Posts: 351 Rep Power: 18	The solution for what? You haven't really provided enough information for anyone to understand your problem.

November 14, 2020, 17:31		#6
aero_head Senior Member Kira Join Date: Nov 2020 Location: Canada Posts: 435 Rep Power: 8	Hello RaviTeja, Are you running your simulation in single or double precision? Also, what is the timestep you are using for your simulation?