{"id":16401,"date":"2024-04-24T12:55:04","date_gmt":"2024-04-24T12:55:04","guid":{"rendered":"https:\/\/aerospacerepository.org\/?p=16401"},"modified":"2024-04-24T12:55:06","modified_gmt":"2024-04-24T12:55:06","slug":"low-fidelity-design-and-analysis-of-propulsion-systems-for-high-supersoniccruiser-concepts","status":"publish","type":"post","link":"https:\/\/aerospacerepository.org\/index.php\/2024\/04\/24\/low-fidelity-design-and-analysis-of-propulsion-systems-for-high-supersoniccruiser-concepts\/","title":{"rendered":"Low fidelity design and analysis of propulsion systems for high-supersoniccruiser concepts"},"content":{"rendered":"\n<p><strong>Bora O. Cakir, Ali Can Ispir, Bayindir H. Saracoglu<\/strong><\/p>\n\n\n\n<p><strong>DOI Number XXX-YYY-ZZZ<\/strong><\/p>\n\n\n\n<p><strong>Conference Number HiSST-2022-408<\/strong><\/p>\n\n\n\n<p>Ramjet\/scramjet propulsion is commonly preferred to power supersonic &amp; hypersonic vehicles for cruis-<br>ing faster than Mach 3. This is an elegant solution owing to the lean architecture which does not embody<br>any rotating parts. Although the geometry of the engine is simple as compared to turbo-based engines,<br>the flow physics through the engine duct is quite complex and, the flow speeds modulate between the<br>supersonic and subsonic regimes. The design and performance analysis of such engine configura-<br>tions are vital to make sure that propulsion systems can satisfy the flight trajectory requirements. In the<br>present study, a low fidelity design and analysis methodology is introduced to investigate the propulsive<br>performance characterizations of different design choices on intake configurations, providing complete<br>propulsive flow path simulations via subsonic combustion, thermal choke phenomena and ideal expan-<br>sion through the nozzle.<\/p>\n\n\n\n<p><a href=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2024\/04\/HiSST-2022-408.pdf\">Read the full paper here<\/a><\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>Bora O. Cakir, Ali Can Ispir, Bayindir H. Saracoglu<\/b><\/p>\n<p>DOI Number XXX-YYY-ZZZ<\/p>\n<p>Conference Number HiSST-2022-408<\/p>\n","protected":false},"author":2,"featured_media":0,"comment_status":"open","ping_status":"open","sticky":false,"template":"","format":"standard","meta":{"footnotes":""},"categories":[1006],"tags":[1307,1303,1305,1306,1304],"class_list":["post-16401","post","type-post","status-publish","format-standard","hentry","category-hisst-2022","tag-detailed-chemistry","tag-high-speed-intake-design","tag-propulsive-performance","tag-ramjet-en-gine","tag-reduced-order-modeling","category-1006","description-off"],"_links":{"self":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/16401","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=16401"}],"version-history":[{"count":1,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/16401\/revisions"}],"predecessor-version":[{"id":16403,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/16401\/revisions\/16403"}],"wp:attachment":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/media?parent=16401"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/categories?post=16401"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/tags?post=16401"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}