{"id":17008,"date":"2024-06-03T11:56:45","date_gmt":"2024-06-03T11:56:45","guid":{"rendered":"https:\/\/aerospacerepository.org\/?p=17008"},"modified":"2025-09-15T13:07:38","modified_gmt":"2025-09-15T13:07:38","slug":"observation-of-hydrogen-combustion-characteristics-in-a-scramjet-combustor-based-on-cavity-type","status":"publish","type":"post","link":"https:\/\/aerospacerepository.org\/index.php\/2024\/06\/03\/observation-of-hydrogen-combustion-characteristics-in-a-scramjet-combustor-based-on-cavity-type\/","title":{"rendered":"Observation of Hydrogen Combustion Characteristics in a Scramjet Combustor Based on Cavity Type"},"content":{"rendered":"\n<p><strong>Geon Wook YIM, Hyoung Jin LEE<\/strong><\/p>\n\n\n\n<p><strong>DOI Number: N\/A<\/strong><\/p>\n\n\n\n<p><strong>Conference number: HiSST-2024-180<\/strong><\/p>\n\n\n\n<p>In a scramjet combustor, combustion characteristics were observed based on the L\/D ratio of the cavity under equivalent equivalence ratio conditions. Combustion experiments were conducted at a Mach number of 2.0 and a pre-temperature of 1400 K inside the combustor. Hydrogen was used as the fuel, and the L\/D ratios of the cavity were set at 7 and 12. The equivalence ratio was maintained at 0.4. The experimental results revealed a mode transition at L\/D ratios of 7 and 12. At L\/D 12, a mode transition occurred between cavity shear-layer stabilized combustion and cavity shear-layer\/recirculation stabilized combustion. At L\/D 7, a similar combustion mode transition occurred as at L\/D 12, but the Jet-wake combustion mode also manifested. According to the experimental results, under the same equivalence ratio, L\/D 12 exhibited more stable characteristics.<\/p>\n\n\n\n<p><a href=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2024\/06\/HiSST-2024-180.pdf\">Read the full paper here<\/a><\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>Geon Wook YIM, Hyoung Jin LEE<\/b><\/p>\n<p>DOI Number: N\/A<\/p>\n<p>Conference number: HiSST-2024-180<\/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":[1691,712,614],"class_list":["post-17008","post","type-post","status-publish","format-standard","hentry","category-events","category-11-hisst-2024","category-propulsion-systems-and-components-11-hisst-2024","tag-cavity","tag-combustion","tag-scramjet","category-993","category-1407","category-1414","description-off"],"_links":{"self":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/17008","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=17008"}],"version-history":[{"count":2,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/17008\/revisions"}],"predecessor-version":[{"id":20841,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/17008\/revisions\/20841"}],"wp:attachment":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/media?parent=17008"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/categories?post=17008"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/tags?post=17008"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}