{"id":23272,"date":"2025-10-26T12:17:34","date_gmt":"2025-10-26T12:17:34","guid":{"rendered":"https:\/\/aerospacerepository.org\/?p=23272"},"modified":"2025-10-26T12:17:36","modified_gmt":"2025-10-26T12:17:36","slug":"low-cost-supersonic-combustion-modeling-for-hydrogen-transverse-injection","status":"publish","type":"post","link":"https:\/\/aerospacerepository.org\/index.php\/2025\/10\/26\/low-cost-supersonic-combustion-modeling-for-hydrogen-transverse-injection\/","title":{"rendered":"Low-cost supersonic combustion modeling for hydrogen transverse injection"},"content":{"rendered":"\n<p><strong>Pedro Paulo Batista De ARAUJO, Yan Da Silva PEDRONI, Jo\u00e3o Vitor Marques Brito De SIQUEIRA, F\u00e1bio Henrique Eug\u00eanio RIBEIRO, Angelo PASSARO, Amanda CHENU ROMANO, Leda Marise VIALTA<\/strong><\/p>\n\n\n\n<p><strong>DOI Number: N\/A<\/strong><\/p>\n\n\n\n<p><strong>Conference number: HiSST-2025-014<\/strong><\/p>\n\n\n\n<p>This study presents a comparison between a low-cost supersonic combustion modeling approach and CFD simulations validated against experimental data obtained from shock tunnel testing. The CFD analysis employs a finite-rate chemistry model without turbulence-chemistry interaction (no TCI), using the SST k\u2013\u03c9 turbulence model in a Reynolds-Averaged Navier-Stokes equation (RANS) approach. Three combustor geometries, with and without flame holder, were evaluated. Parameters of combustion efficiency were derived from CFD simulations. Pressure, temperature, and Mach number were compared to assess the accuracy of the proposed low-cost methodology.<\/p>\n\n\n\n<p><a href=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2025\/10\/HISST2025_14_paper.pdf\">Read the full paper here<\/a><\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>Pedro Paulo Batista De ARAUJO, Yan Da Silva PEDRONI, Jo\u00e3o Vitor Marques Brito De SIQUEIRA, F\u00e1bio Henrique Eug\u00eanio RIBEIRO, Angelo PASSARO, Amanda CHENU ROMANO, Leda Marise VIALTA<\/b><\/p>\n<p>DOI Number: N\/A<\/p>\n<p>Conference number: HiSST-2025-014<\/p>\n","protected":false},"author":2,"featured_media":0,"comment_status":"open","ping_status":"open","sticky":false,"template":"","format":"standard","meta":{"footnotes":""},"categories":[993,3361,3363],"tags":[1691,1171,3751,470],"class_list":["post-23272","post","type-post","status-publish","format-standard","hentry","category-events","category-1-hisst-2025","category-propulsion-systems-components","tag-cavity","tag-combustion-efficiency","tag-low-cost-tool","tag-supersonic-combustion","category-993","category-3361","category-3363","description-off"],"_links":{"self":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/23272","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=23272"}],"version-history":[{"count":1,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/23272\/revisions"}],"predecessor-version":[{"id":23274,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/23272\/revisions\/23274"}],"wp:attachment":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/media?parent=23272"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/categories?post=23272"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/tags?post=23272"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}