{"id":16990,"date":"2024-06-03T10:55:52","date_gmt":"2024-06-03T10:55:52","guid":{"rendered":"https:\/\/aerospacerepository.org\/?p=16990"},"modified":"2025-09-15T13:11:26","modified_gmt":"2025-09-15T13:11:26","slug":"theoretical-analysis-of-interaction-between-rotating-detonation-wave-and-upstream-flow-field","status":"publish","type":"post","link":"https:\/\/aerospacerepository.org\/index.php\/2024\/06\/03\/theoretical-analysis-of-interaction-between-rotating-detonation-wave-and-upstream-flow-field\/","title":{"rendered":"Theoretical Analysis of Interaction between Rotating Detonation Wave and Upstream Flow Field"},"content":{"rendered":"\n<p><strong>Sijia Gao, Han Peng<em>, <\/em>Yue Huang, Zhipeng Sun, Yancheng You<\/strong><\/p>\n\n\n\n<p><strong>DOI Number: N\/A<\/strong><\/p>\n\n\n\n<p><strong>Conference number: HiSST-2024-173<\/strong><\/p>\n\n\n\n<p>In order to investigate the interaction between the detonation wave and the upstream airflow, a<br>non-premixed air-breathing rotating detonation combustor with an axial inlet was simulated by using<br>the Navier-Stokes equation of two-dimensional unsteady reaction, a complete structure of rotating<br>detonation wave and upstream flow field was obtained, and the interaction between the detonation<br>wave and the upstream airflow was analyzed by a combination of equation derivation and numerical<br>simulation. The equations for calculating the airflow velocity after the forward shock wave and the<br>height of detonation wave were derived and verified. The results show that the rotating detonation<br>wave would trigger the forward shock wave propagating in the upstream, and the velocity would be<br>weakened and the direction would be deflected of the airflow passing through the forward shock wave.<br>If the airflow velocity drops to a negative value after passing the forward shock wave, there will be no<br>air injection into the combustor. The velocity of the airflow after the forward shock wave is inversely<br>proportional to the velocity of the detonation wave, the temperature of the incoming airflow and the<br>pressure ratio at the forward shock wave. The angle of the forward shock wave is inversely proportional<br>to the velocity of the detonation wave. The interaction between detonation wave and incoming flow is<br>summarized, the higher the intensity of the detonation wave, the slower the recovery time of the airflow<br>after the forward shock wave, and the lower the height of the detonation wave.<\/p>\n\n\n\n<p><a href=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2024\/06\/HiSST-2024-173.pdf\">Read the full paper here<\/a><\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>Sijia Gao, Han Peng, Yue Huang, Zhipeng Sun, Yancheng You<\/b><\/p>\n<p>DOI Number: N\/A<\/p>\n<p>Conference number: HiSST-2024-173<\/p>\n","protected":false},"author":2,"featured_media":0,"comment_status":"open","ping_status":"open","sticky":false,"template":"","format":"standard","meta":{"footnotes":""},"categories":[993,1409,1407],"tags":[1677,1680,1678,1679,1681],"class_list":["post-16990","post","type-post","status-publish","format-standard","hentry","category-events","category-high-speed-aerodynamics-and-aerothermodynamics-11-hisst-2024","category-11-hisst-2024","tag-air-breathing-rotating-detonation-engine","tag-detonation-wave-height","tag-forward-shock-wave","tag-incoming-flow","tag-theoretical-derivation","category-993","category-1409","category-1407","description-off"],"_links":{"self":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/16990","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=16990"}],"version-history":[{"count":2,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/16990\/revisions"}],"predecessor-version":[{"id":20853,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/16990\/revisions\/20853"}],"wp:attachment":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/media?parent=16990"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/categories?post=16990"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/tags?post=16990"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}