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how can make normal shock in the nozzle at inlet B.C : Pressure Far field |
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August 18, 2015, 10:54 |
how can make normal shock in the nozzle at inlet B.C : Pressure Far field
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#1 |
New Member
Hongseok Yoo
Join Date: Mar 2014
Posts: 3
Rep Power: 12 |
hi, everyone. i have some questions.
first, im using B.C Pressure inlet/outlet, i can make normal shock in the nozzle. its unsteady flow. so normal shock is keep moving forward. but, im using B.C Pressure Far field / Pressure outlet, i cant make normal shock in the nozzle. it's just supersonic flow in the nozzle and oblique shock is appear i wanna make inlet flow mach number 3.0 and outlet flow mach number 0.4. so, changing the supersonic flow to subsonic flow. but i cant do it. i founded some Sentence from the fluent help mannual. Pressure outlet boundary conditions require the specification of a static (gauge) pressure at the outlet boundary. The value of the specified static pressure is used only while the flow is subsonic. Should the flow become locally supersonic, the specified pressure will no longer be used; pressure will be extrapolated from the flow in the interior. so, i understand, pressure outlet's gauge pressure is ignored at supersonic flow. how can make normal shock in the nozzle at inlet B.C : Pressure Far field?? Perhaps... Pressure Far field is not acceptable?? any suggestion. please help me. |
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March 3, 2016, 09:26 |
same problem
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#2 | |
New Member
Join Date: Feb 2011
Posts: 4
Rep Power: 15 |
Quote:
I have the same problem have you solved yours can you help me can someone pleaaase help me |
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May 8, 2016, 06:16 |
Help please
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#3 |
New Member
Join Date: Feb 2011
Posts: 4
Rep Power: 15 |
No one has any suggestions?
it became an annoying problem I am trying to fix inlet and outlet mach numbers in a converging-diverging diffuser, the parameters are set by the mean of pressure inlet/outlet boundaries. the values at these boundaries are pre-calculated by the inviscid quasi 2dimensional relations and normal and oblique shock relations. the problem is that after some iterations, mach number at the inlet decreases to subsonic and the supersonic diffuser acts like a nuzzle so the flow enters subsonic and leaves the channel supersonic, which exactly the opposite of what i want to simulate please, help me |
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normal shock, pressure outlet, supersonic flow, terminal shock |
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