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February 14, 2021, 13:11 |
Simulation in the chamber of hybrid rocket
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#1 |
New Member
Kanami
Join Date: Dec 2020
Location: Japan
Posts: 2
Rep Power: 0 |
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. Kanami Last edited by Caramel; February 15, 2021 at 23:59. |
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Tags |
ansys, chamber, fluent, hybrid rocket |
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