{"id":17300,"date":"2024-06-06T14:15:51","date_gmt":"2024-06-06T14:15:51","guid":{"rendered":"https:\/\/aerospacerepository.org\/?p=17300"},"modified":"2025-09-11T12:46:32","modified_gmt":"2025-09-11T12:46:32","slug":"numerical-study-of-turbulent-combustion-in-high-mach-number-scramjet-engine-with-thermodynamic-non-equilibrium-effect","status":"publish","type":"post","link":"https:\/\/aerospacerepository.org\/index.php\/2024\/06\/06\/numerical-study-of-turbulent-combustion-in-high-mach-number-scramjet-engine-with-thermodynamic-non-equilibrium-effect\/","title":{"rendered":"Numerical Study of Turbulent Combustion in High Mach Number Scramjet Engine with Thermodynamic Non-equilibrium Effect"},"content":{"rendered":"\n<p><strong>Hai FENG, Tai JIN, Kun WU<\/strong><\/p>\n\n\n\n<p><strong>DOI Number: N\/A<\/strong><\/p>\n\n\n\n<p><strong>Conference number: HiSST-2024-328<\/strong><\/p>\n\n\n\n<p>Thermodynamic non-equilibrium effect has a significant impact on hypersonic aircraft and must be taken into consideration in numerical computations. Numerical simulations of a Mach 12 flight condition scramjet engine were conducted using both thermodynamic equilibrium models and Park&#8217;s dual-temperature non-equilibrium model. The results indicate that, compared to equilibrium state calculations, non-equilibrium effects lead to a rearward shift in the wave system position, resulting in a noticeable reduction in peak pressure between shock waves, with a more pronounced impact on the reaction flow. The non-equilibrium Ttr temperature field is generally similar to the equilibrium state. Thermodynamic non-equilibrium effects lead to a slight reduction in Ttr. In the non-equilibrium state, the combustion efficiency at the outlet section of the combustion chamber is higher, indicating that thermodynamic non-equilibrium effects enhance the extent of the reaction.<\/p>\n\n\n\n<p><a href=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2024\/06\/HiSST-2024-328.pdf\">Read the full paper here<\/a><\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>Hai FENG, Tai JIN, Kun WU<\/b><\/p>\n<p>DOI Number: N\/A<\/p>\n<p>Conference number: HiSST-2024-328<\/p>\n","protected":false},"author":2,"featured_media":0,"comment_status":"open","ping_status":"open","sticky":false,"template":"","format":"standard","meta":{"footnotes":""},"categories":[993,1407,1414],"tags":[440,614,1881,1882],"class_list":["post-17300","post","type-post","status-publish","format-standard","hentry","category-events","category-11-hisst-2024","category-propulsion-systems-and-components-11-hisst-2024","tag-hypersonic","tag-scramjet","tag-thermodynamic-non-equilibrium","tag-wave-structure","category-993","category-1407","category-1414","description-off"],"_links":{"self":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/17300","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=17300"}],"version-history":[{"count":2,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/17300\/revisions"}],"predecessor-version":[{"id":20557,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/17300\/revisions\/20557"}],"wp:attachment":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/media?parent=17300"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/categories?post=17300"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/tags?post=17300"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}