Supersonic Intake Starting

Obad · November 5, 2016, 17:29

Hi guys,

I'm trying to simulate the 3D flow through a supersonic intake of a turbojet engine. The flow through the engine itself is not simulated so that the inlet is truncated after the subsonic diffusor section.

My problem is that I don't manage to get a (supercritical) started solution for the intake flow. The flow is initialized with the supersonic farfield conditions. The boundary condition that I'm applying to the truncated intake outflow is a fixed static pressure (since the flow there is supposed to be subsonic).
However, if I specify the given static pressure at this plane the calculation immediately crashes after startup. Starting the solution with a backpressure similar to the farfield conditions works.

Does anyone know the right approach to this problem?

I already tried to ramp up the backpressure, however without satisfying results.

rangesh91 · November 17, 2017, 11:48

Hi Obad,

I have been having the same problem. I am trying to simulate a 2D supersonic intake (https://arc.aiaa.org/doi/abs/10.2514...ournalCode=jpp) with rhocentralFoam solver in OpenFoam, with a fixed back pressure condition.
The shock always moves to the inlet domain (unstarting, I believe). Did you find a solution to your problem ?

abubakar65 · September 17, 2019, 14:33

I saw a new item from SUPERSONIC INC with FCCID 2AC5R-SC-904BTK and name is Microphone Speaker .it is osum. I think you should check it out. https://fccid.io/2AC5R-SC-904BTK

November 5, 2016, 17:29	Supersonic Intake Starting	#1
Obad Member Obad Join Date: Sep 2013 Posts: 42 Rep Power: 12	Hi guys, I'm trying to simulate the 3D flow through a supersonic intake of a turbojet engine. The flow through the engine itself is not simulated so that the inlet is truncated after the subsonic diffusor section. My problem is that I don't manage to get a (supercritical) started solution for the intake flow. The flow is initialized with the supersonic farfield conditions. The boundary condition that I'm applying to the truncated intake outflow is a fixed static pressure (since the flow there is supposed to be subsonic). However, if I specify the given static pressure at this plane the calculation immediately crashes after startup. Starting the solution with a backpressure similar to the farfield conditions works. Does anyone know the right approach to this problem? I already tried to ramp up the backpressure, however without satisfying results.

September 17, 2019, 14:33	Supersonic	#3
abubakar65 New Member abubakar Join Date: Sep 2019 Posts: 1 Rep Power: 0	I saw a new item from SUPERSONIC INC with FCCID 2AC5R-SC-904BTK and name is Microphone Speaker .it is osum. I think you should check it out. https://fccid.io/2AC5R-SC-904BTK

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November 17, 2017, 11:48		#2
rangesh91 New Member -- Select -- Join Date: Feb 2014 Posts: 2 Rep Power: 0	Hi Obad, I have been having the same problem. I am trying to simulate a 2D supersonic intake (https://arc.aiaa.org/doi/abs/10.2514...ournalCode=jpp) with rhocentralFoam solver in OpenFoam, with a fixed back pressure condition. The shock always moves to the inlet domain (unstarting, I believe). Did you find a solution to your problem ?