{"id":13628,"date":"2023-10-26T20:10:12","date_gmt":"2023-10-26T20:10:12","guid":{"rendered":"https:\/\/aerospacerepository.org\/?p=13628"},"modified":"2024-04-22T20:08:17","modified_gmt":"2024-04-22T20:08:17","slug":"the-interaction-of-shock-waves-near-a-cylinder-normal-to-a-blunted-plate","status":"publish","type":"post","link":"https:\/\/aerospacerepository.org\/index.php\/2023\/10\/26\/the-interaction-of-shock-waves-near-a-cylinder-normal-to-a-blunted-plate\/","title":{"rendered":"The interaction of shock waves near a cylinder normal to a blunted plate"},"content":{"rendered":"\n<p><strong>V. Borovoy&nbsp; , V. Mosharov , V. Radchenko , and A. Skuratov<\/strong><\/p>\n\n\n\n<p><strong>DOI Number XXX-YYY-ZZZ<\/strong><\/p>\n\n\n\n<p><strong>Conference Number HiSST2018_47801549<\/strong><\/p>\n\n\n\n<div style=\"height:50px\" aria-hidden=\"true\" class=\"wp-block-spacer\"><\/div>\n\n\n\n<p>An experimental study of the interaction of shock waves near a cylinder perpendicular to a blunted plate was carried out. The experiments were made in the Ludwig wind tunnel at Mach number M\u221e=5 and different Reynolds numbers Re\u221eL in the range from 0.6 107 to 4.0 107 . The heat fluxes to the model surface, measured using Temperature Sensitive Paint (TSP), were analyzed. The influence of the plate blunting radius and the distance of cylindrical obstacle from plate leading edge on the gas flow are studied.<\/p>\n\n\n\n<div style=\"height:50px\" aria-hidden=\"true\" class=\"wp-block-spacer\"><\/div>\n\n\n\n<p><a href=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2023\/10\/hisst-2018_47801549.pdf\" data-type=\"link\" data-id=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2023\/10\/hisst-2018_47801549.pdf\">Read the full paper &gt; <\/a><\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>V. Borovoy, V. Mosharov , V. Radchenko , and A. Skuratov <\/b><\/p>\n<p>DOI Number XXX-YYY-ZZZ<\/p>\n<p>Conference Number HiSST 2018_47801549<\/p>\n","protected":false},"author":1,"featured_media":0,"comment_status":"open","ping_status":"open","sticky":false,"template":"","format":"standard","meta":{"footnotes":""},"categories":[996,994,198,999],"tags":[513,988,989,708],"class_list":["post-13628","post","type-post","status-publish","format-standard","hentry","category-high-speed-aerodynamics-and-aerothermodynamics","category-hisst-2018","category-hypersonic-aerodynamics","category-materials-and-structures-hisst-2018","tag-heat-transfer-2","tag-ludwieg-wind-tunnel","tag-shock-waves-interference","tag-temperature-sensitive-paint-tsp","category-996","category-994","category-198","category-999","description-off"],"_links":{"self":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/13628","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\/1"}],"replies":[{"embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/comments?post=13628"}],"version-history":[{"count":7,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/13628\/revisions"}],"predecessor-version":[{"id":16355,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/13628\/revisions\/16355"}],"wp:attachment":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/media?parent=13628"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/categories?post=13628"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/tags?post=13628"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}