{"id":17326,"date":"2024-06-07T09:15:16","date_gmt":"2024-06-07T09:15:16","guid":{"rendered":"https:\/\/aerospacerepository.org\/?p=17326"},"modified":"2025-09-21T13:38:22","modified_gmt":"2025-09-21T13:38:22","slug":"a-numerical-simulation-on-the-unsteady-flow-in-a-gch4-gox-small-thrust-chamber","status":"publish","type":"post","link":"https:\/\/aerospacerepository.org\/index.php\/2024\/06\/07\/a-numerical-simulation-on-the-unsteady-flow-in-a-gch4-gox-small-thrust-chamber\/","title":{"rendered":"A Numerical Simulation on the Unsteady Flow in a GCH4-GOx Small Thrust Chamber"},"content":{"rendered":"\n<p><strong>Hong Yeong PARK, Yun Hyeong KANG, Chang Han BAE, Jeong Soo KIM<\/strong><\/p>\n\n\n\n<p><strong>DOI Number: 10.82241\/ceas-hisst-2024-341<\/strong><\/p>\n\n\n\n<p><strong>Conference number: HiSST-2024-341<\/strong><\/p>\n\n\n\n<p>A numerical simulation was conducted to scrutinize an unsteady physics which shows a stepwise increase of thrust performance in the later part of the combustion under the fuel-rich conditions. The nozzle outflow region was included in the calculation domain to reflect the influence of the atmospheric pressure condition. The flow field was analyzed using the RANS (Reynolds-Averaged Navier-Stokes) equation, and a non-adiabatic diffusion flamelet with 21 species and 84 reactions was applied to simulate the flame structure. As a result, the pressure and thrust calculated by the simulations were in good agreement with the experimental ones. However, an abrupt increase of thrust performance<br>observed at the later stage of the combustion duration was not clearly captured in the transient results. This indicates a limitation of the combustion model employed in calculating the abnormal phenomenon of thrust change.<\/p>\n\n\n\n<p><a href=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2024\/06\/HiSST-2024-341.pdf\">Read the full paper here<\/a><\/p>\n\n\n\n<p><\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>Hong Yeong PARK, Yun Hyeong KANG, Chang Han BAE, Jeong Soo KIM<\/b><\/p>\n<p>DOI Number: https:\/\/doi.org\/10.82241\/ceas-hisst-2024-341<\/p>\n<p>Conference number: HiSST-2024-341<\/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":[1898,1897,1899],"class_list":["post-17326","post","type-post","status-publish","format-standard","hentry","category-events","category-11-hisst-2024","category-propulsion-systems-and-components-11-hisst-2024","tag-cfd-computational-fluid-dynamics","tag-film-cooling-2","tag-multi-phase-flow","category-993","category-1407","category-1414","description-off"],"_links":{"self":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/17326","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=17326"}],"version-history":[{"count":4,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/17326\/revisions"}],"predecessor-version":[{"id":21210,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/17326\/revisions\/21210"}],"wp:attachment":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/media?parent=17326"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/categories?post=17326"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/tags?post=17326"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}