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Why my calculation of Mach number is not the same as fluent |
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#1 |
New Member
iiran
Join Date: Jul 2021
Posts: 21
Rep Power: 5 ![]() |
Hello, everyone. I have a problem when I want to verify my inlet data on the supersonic fluid.
I use the equation “Mach number = Velocity / (1.4 * R * static temperature)”, and what amazing me is that when I substitute the following data into the equation, I find the Mach number is 2.4970 (R is 287.15 for air), but fluent shows that the mach number is 2.439456. So I wonder why this happens and how to get the real answer as fluent? Thank you in advance! |
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#2 |
New Member
iiran
Join Date: Jul 2021
Posts: 21
Rep Power: 5 ![]() |
Now I understand why , this because it uses the average number, I don't know how to delete this post, thank you for you reading.
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Tags |
supersonic flow, supersonic inlet |
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