{"id":298184,"date":"2023-08-04T12:47:37","date_gmt":"2023-08-04T12:47:37","guid":{"rendered":"\/forum\/forums\/topic\/2d-supersonic-inlet\/"},"modified":"2023-09-13T07:44:18","modified_gmt":"2023-09-13T07:44:18","slug":"2d-supersonic-inlet","status":"closed","type":"topic","link":"https:\/\/innovationspace.ansys.com\/forum\/forums\/topic\/2d-supersonic-inlet\/","title":{"rendered":"2D Supersonic Inlet"},"content":{"rendered":"<p>Hello everybody,<\/p>\n<p>I am trying to simulate a 2D supersonic inlet and analyze the effect of the imposition of a certain back-pressure ratio between the inlet and the outlet.<\/p>\n<p>Here is the geometry and mesh I am simulating:<\/p>\n<p><img decoding=\"async\" src=\"\/forum\/wp-content\/uploads\/sites\/2\/2023\/08\/04-08-2023-1691151850-200K.png\" alt=\"\"><\/p>\n<p>The inlet section is on the left and the outlet section is on the right.<\/p>\n<p>I would like to obtain a full structured mesh, even though this was the best result I was able to get to. I have used either the number of divisions&#8217; option, for each and every edge of the geometry, and the inflation option. The wall y+ was in between 0.0014 and 5.<\/p>\n<p>Any suggestion about how to improve the mesh quality would be really welcome.<\/p>\n<p>Then I moved to Fluent and I ended up with results that are not that good. Here are the boundary conditions I imposed:<\/p>\n<p><img decoding=\"async\" src=\"\/forum\/wp-content\/uploads\/sites\/2\/2023\/08\/04-08-2023-1691152778-InkedInked200K2o.jpg\" alt=\"\"><\/p>\n<p>Unfortunately there is no shockwave generated in the channel. As you can see in the schlieren and Mach contours:<\/p>\n<p><img decoding=\"async\" src=\"\/forum\/wp-content\/uploads\/sites\/2\/2023\/08\/04-08-2023-1691153067-Schlieren.png\" alt=\"\"><\/p>\n<p><img decoding=\"async\" src=\"\/forum\/wp-content\/uploads\/sites\/2\/2023\/08\/04-08-2023-1691153081-Mach.png\" alt=\"\"><\/p>\n<p>The back-pressure ratio (the ration between the back pressure outlet and the inlet pressure) is 0 in this case.<\/p>\n<p>There should be a very clear shockwave pattern in the channel, do you have any idea why I am getting it wrong? What adjustements can I introduce?<\/p>\n","protected":false},"template":"","class_list":["post-298184","topic","type-topic","status-closed","hentry","topic-tag-2d","topic-tag-cfd","topic-tag-fluent","topic-tag-mesh","topic-tag-supersonic","topic-tag-SupersonicNozzleFlow-1"],"aioseo_notices":[],"aioseo_head":"\n\t\t<!-- All in One SEO 4.9.10 - aioseo.com -->\n\t<meta name=\"description\" content=\"Hello everybody,I am trying to simulate a 2D supersonic inlet and analyze the effect of the imposition of a certain back-pressure ratio between the inlet and the outlet.Here is the geometry and mesh I am simulating:The inlet section is on the left and the outlet section is on the right.I would like to obtain a\" \/>\n\t<meta name=\"robots\" content=\"max-image-preview:large\" \/>\n\t<link rel=\"canonical\" href=\"https:\/\/innovationspace.ansys.com\/forum\/forums\/topic\/2d-supersonic-inlet\/\" \/>\n\t<meta name=\"generator\" content=\"All in One SEO (AIOSEO) 4.9.10\" \/>\n\t\t<meta 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