{"id":23215,"date":"2025-10-26T11:15:41","date_gmt":"2025-10-26T11:15:41","guid":{"rendered":"https:\/\/aerospacerepository.org\/?p=23215"},"modified":"2025-10-26T11:15:42","modified_gmt":"2025-10-26T11:15:42","slug":"thermal-non-equilibrium-effects-in-the-inviscid-flow-within-high-mach-number-inlets","status":"publish","type":"post","link":"https:\/\/aerospacerepository.org\/index.php\/2025\/10\/26\/thermal-non-equilibrium-effects-in-the-inviscid-flow-within-high-mach-number-inlets\/","title":{"rendered":"Thermal non-equilibrium effects in the inviscid flow within high Mach number inlets"},"content":{"rendered":"\n<p><strong>Dengke LI, Bo SUN, Xiong CHEN<\/strong><\/p>\n\n\n\n<p><strong>DOI Number: N\/A<\/strong><\/p>\n\n\n\n<p><strong>Conference number: HiSST-2025-056<\/strong><\/p>\n\n\n\n<p>The thermal non-equilibrium caused by the high temperature has significant impacts on the inviscid flows through the hypersonic inlets. However, there is limited research available that provides a comprehensive understanding of the impacts of thermal non-equilibrium on the flows of the inlets with wide design constraints. To explore the thermal non-equilibrium effects within the high Mach number inlets, the inviscid flows obtained by method of non-equilibrium characteristics are compared with the flow calculated under th1e calorically perfect gas (CPG) assumption. The results reveal that the impacts of thermal non-equilibrium on the outlet Mach number and static temperature intensify with the<br>increasing flight Mach number, compression level and capture height. The relative discrepancies in outlet Mach number and static temperature that induced by thermal non-equilibrium can exceed 10%. Those discrepancies stem from the redistribution of internal energy modes in the thermal non-equilibrium flow. It is found that the discrepancy in outlet static temperature shows a quasi-equal relationship with ev \/ e at the outlet section, while the discrepancy in outlet Mach number exhibits a power-law correlation with ev \/ e at the outlet section. Due to the scale effects of thermal non-equilibrium, the discrepancy in outlet Mach number rises from 4% to 10.4% as the capture height increases from 0.125 m to 2 m. The above insights provide valuable reference for the thermal non-equilibrium effects in the inviscid design and evaluation of high Mach number inlet for scramjets and<br>oblique detonation engines.<\/p>\n\n\n\n<p><a href=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2025\/10\/HISST2025_56_paper.pdf\">Read the full paper here<\/a><\/p>\n\n\n\n<p><\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>Dengke LI, Bo SUN, Xiong CHEN<\/b><\/p>\n<p>DOI Number: N\/A<\/p>\n<p>Conference number: HiSST-2025-056<\/p>\n","protected":false},"author":2,"featured_media":0,"comment_status":"open","ping_status":"open","sticky":false,"template":"","format":"standard","meta":{"footnotes":""},"categories":[993,3367,3361],"tags":[3721,3722,3723,3724,1191],"class_list":["post-23215","post","type-post","status-publish","format-standard","hentry","category-events","category-high-speed-aerodynamics-and-aerothermodynamics-with-application-to-hypersonic-regimes","category-1-hisst-2025","tag-high-mach-number-inlet","tag-inviscid-flow","tag-scale-effects","tag-scramjets","tag-thermal-non-equilibrium","category-993","category-3367","category-3361","description-off"],"_links":{"self":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/23215","targetHints":{"allow":["GET"]}}],"collection":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts"}],"about":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/types\/post"}],"author":[{"embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/users\/2"}],"replies":[{"embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/comments?post=23215"}],"version-history":[{"count":1,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/23215\/revisions"}],"predecessor-version":[{"id":23217,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/23215\/revisions\/23217"}],"wp:attachment":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/media?parent=23215"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/categories?post=23215"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/tags?post=23215"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}