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#1 |
New Member
RaviTeja Gonnabathula
Join Date: Oct 2019
Posts: 10
Rep Power: 7 ![]() |
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
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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#2 |
Senior Member
Join Date: Jul 2009
Posts: 358
Rep Power: 19 ![]() |
Given those values your static pressure is correct.
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#3 |
New Member
RaviTeja Gonnabathula
Join Date: Oct 2019
Posts: 10
Rep Power: 7 ![]() |
Thank you.. what could be the solution
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#4 |
Senior Member
Join Date: Jul 2009
Posts: 358
Rep Power: 19 ![]() |
The solution for what? You haven't really provided enough information for anyone to understand your problem.
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#5 |
New Member
RaviTeja Gonnabathula
Join Date: Oct 2019
Posts: 10
Rep Power: 7 ![]() |
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#6 |
Senior Member
Kira
Join Date: Nov 2020
Location: Canada
Posts: 435
Rep Power: 9 ![]() |
Hello RaviTeja,
Are you running your simulation in single or double precision? Also, what is the timestep you are using for your simulation? |
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Tags |
boundary condition, fluent, freestream pressure, pressure farfield |
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