{"id":307063,"date":"2023-09-16T07:55:39","date_gmt":"2023-09-16T07:55:39","guid":{"rendered":"\/forum\/forums\/topic\/residuals-not-converging-2d-supesonic-inlet\/"},"modified":"2023-09-16T07:56:43","modified_gmt":"2023-09-16T07:56:43","slug":"residuals-not-converging-2d-supesonic-inlet","status":"closed","type":"topic","link":"https:\/\/innovationspace.ansys.com\/forum\/forums\/topic\/residuals-not-converging-2d-supesonic-inlet\/","title":{"rendered":"Residuals not converging (2D supesonic inlet)"},"content":{"rendered":"

Hello everybody,<\/p>\n

I am trying to simulate a supersonic flow throguh an air intake.<\/p>\n

The final aim of the project is to reproduce the results reported in a reference paper, but my residuals are not converging.<\/p>\n

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The mesh I have used for the simulation is the following:<\/p>\n

\"\"<\/a><\/p>\n

The density-based (coupled) implicit double precision Fluent solver has been set.<\/p>\n

For the inlet I set a farfield bc with a Mach number equals to 2.41.<\/p>\n

For the outlet I set a pressure-outlet bc with zero pressure.<\/p>\n

The CFL was fixed at 0.5.<\/p>\n

All of these conditions come from the reference paper.<\/p>\n

I have also tried to switch to a pressure-based solver, but the solution get even worse.<\/p>\n

What might be the issue?<\/p>\n","protected":false},"template":"","class_list":["post-307063","topic","type-topic","status-closed","hentry","topic-tag-CFDSolver-1","topic-tag-residuals","topic-tag-supersonic","topic-tag-supersonic-flow-1"],"aioseo_notices":[],"aioseo_head":"\n\t\t\n\t\n\t\n\t\n\t\n\t\t\n\t\t\n\t\t\n\t\t\n\t\t\n\t\t\n\t\t\n\t\t\n\t\t\n\t\t\n\t\t\n\t\t\n\t\t\n\t\t\n\t\t