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Simulation in the chamber of hybrid rocket

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Old   February 14, 2021, 12:11
Default Simulation in the chamber of hybrid rocket
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Hello, everyone.

I am new to dealing with fluent.
Since no one in my lab has done numerical analysis in the past, I am having a lot of trouble in proceeding with the analysis.

I am doing a numerical analysis of the inside of the combustion chamber of a hybrid rocket in 2D. (Please refer to the picture for the model. The model is for an axis.)
I am assuming that the oxidizer (oxygen) flows out of the inlet on the right, and the fuel (kerosene air mixture) melts and flows out of the upper and lower inlets.

(1) I am not sure whether to use the fuel inflow as velocity or mass flow. I have calculated the flux and mass flow rate for the fuel based on the fuel recession rate, but which should I use?

(2) When I run the numerical analysis with the fuel as flow velocity, the combustion reaction does not occur properly. What should I do to set the analysis conditions?

I would like to thank everybody in advance.
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File Type: png general.png (120.2 KB, 10 views)
File Type: png models.png (146.8 KB, 11 views)

Last edited by Caramel; February 15, 2021 at 22:59.
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ansys, chamber, fluent, hybrid rocket

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