{"id":13170,"date":"2023-10-06T12:57:28","date_gmt":"2023-10-06T12:57:28","guid":{"rendered":"https:\/\/aerospacerepository.org\/?p=13170"},"modified":"2024-05-03T15:00:22","modified_gmt":"2024-05-03T15:00:22","slug":"numerical-simulation-assistant-design-of-the-near-field-sonic-boom-signature-measurement-system-for-avic-aris-fl-60-wind-tunnel","status":"publish","type":"post","link":"https:\/\/aerospacerepository.org\/index.php\/2023\/10\/06\/numerical-simulation-assistant-design-of-the-near-field-sonic-boom-signature-measurement-system-for-avic-aris-fl-60-wind-tunnel\/","title":{"rendered":"Numerical simulation assistant design of the near-field sonic boom signature measurement system for AVIC ARI\u2019s FL-60 wind tunnel"},"content":{"rendered":"\n<p><strong>Leng Yan , Liu Zhongchen , Qian Zhansen<\/strong><\/p>\n\n\n\n<p><strong>DOI Number XXX-YYY-ZZZ<\/strong><\/p>\n\n\n\n<p><strong>Conference Number HiSST 2018_810923<\/strong><\/p>\n\n\n\n<div style=\"height:50px\" aria-hidden=\"true\" class=\"wp-block-spacer\"><\/div>\n\n\n\n<p>In the present paper, we present the design of the near-field sonic boon signature measurement system for AVIC ARI\u2019s FL-60 wind tunnel. FL-60 is a trisonic, blowdown wind tunnel. The Mach number range is of 0.3 to 4.2, and the size of the test section is 1.2mX1.2m. For supersonic condition, a 2-D flexible nozzle with deformable contour flat is utilized to realize Mach number 1.3-4.0 continuously. Most of the design works are by virtue of CFD numerical analysis. In the CFD numerical simulation, the hybrid mesh with a combination of tetrahedral and hexahedral grid is utilized with mesh adaptive strategy to improve the grid resolution. A rail pressure measurement equipment is used in the present work to instead of the traditional pressure probe to improve the measurement efficiency drastically. Based on the conditions of the AVIC ARI\u2019s FL-60 wind tunnel, the size and location of the pressure rail is optimized by the CFD simulation to get the best measured data. And also the effects of flow non-uniform of the tunnel on the sonic boom data are analyzed numerically. The numerical results show that the pressure rail can give satisfied near-field off-body pressure signatures for the present axisymmetric reference model and that will be validated by the reference model tests in the near future.<\/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_810923.pdf\" data-type=\"link\" data-id=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2023\/10\/hisst-2018_810923.pdf\">Download the full paper &gt;<\/a><\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>Leng Yan , Liu Zhongchen , Qian Zhansen<\/b><\/p>\n<p>DOI Number XXX-YYY-ZZZ<br \/>\nConference Number HiSST 2018_810923<\/p>\n","protected":false},"author":1,"featured_media":0,"comment_status":"open","ping_status":"open","sticky":false,"template":"","format":"standard","meta":{"footnotes":""},"categories":[996,994,198,1002],"tags":[507,434,492,506,505,504],"class_list":["post-13170","post","type-post","status-publish","format-standard","hentry","category-high-speed-aerodynamics-and-aerothermodynamics","category-hisst-2018","category-hypersonic-aerodynamics","category-testing-and-evaluation","tag-fl-60-wind-tunnel","tag-hisst-2018","tag-numerical-simulation","tag-off-body-pressure","tag-sonic-boom","tag-wind-tunnel-measurement","category-996","category-994","category-198","category-1002","description-off"],"_links":{"self":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/13170","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=13170"}],"version-history":[{"count":4,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/13170\/revisions"}],"predecessor-version":[{"id":16588,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/13170\/revisions\/16588"}],"wp:attachment":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/media?parent=13170"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/categories?post=13170"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/tags?post=13170"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}