{"id":13541,"date":"2023-10-26T19:16:48","date_gmt":"2023-10-26T19:16:48","guid":{"rendered":"https:\/\/aerospacerepository.org\/?p=13541"},"modified":"2024-05-03T14:07:25","modified_gmt":"2024-05-03T14:07:25","slug":"numerical-investigation-of-total-pressure-pulsations-in-supersonic-trapezoidal-air-intake-using-eddy-resolving-des-method","status":"publish","type":"post","link":"https:\/\/aerospacerepository.org\/index.php\/2023\/10\/26\/numerical-investigation-of-total-pressure-pulsations-in-supersonic-trapezoidal-air-intake-using-eddy-resolving-des-method\/","title":{"rendered":"Numerical investigation of total pressure pulsations in supersonic trapezoidal air intake using eddy resolving DES-method."},"content":{"rendered":"\n<p><strong>Novogorodtsev E.V.<\/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_35801117<\/strong><\/p>\n\n\n\n<div style=\"height:50px\" aria-hidden=\"true\" class=\"wp-block-spacer\"><\/div>\n\n\n\n<p>As a result of flow compression in shock waves, wall friction, eddy formations and other phenomena, the flow in the inlet duct of the supersonic air intake becomes nonstationary and dynamic distortion appears. The dynamic distortion is quantified by the value of the root-mean-square parameter of the total pressure pulsations intensity \u03b5 that is calculated in the control section of the inlet duct. (\u03b5 is pulsating component of the total distortion parameter W= \u035e\u0394\u035e\u03c3\u043e+ \u03b5, \u035e\u0394\u035e\u03c3\u043e is the circumferential distortion parameter). Numerical simulation of unsteady flow was performed using isolated trapezoidal intake configuration equipped with a boundary layer control system on the compression ramp surface. Numerical simulation of steady state flow was presented in [1-4]. To resolve the physical peculiarities of nonstationary turbulent flow, the modern eddy resolving DES (implemented in ANSYS CFX solver) method was applied. For three-dimensional viscous compressible flow computational modeling the geometry and the far field were discretized by means of spatial structured multi-block mesh. The mesh was generated manually, using the ICEM CFD software. To evaluate DES method capability to predict parameter \u03b5 values, numerical results were compared with experimental data. CFD computation data were processed using standard experimental methodology adopted at TsAGI. It was established, that the parameter \u03b5 values, obtained with CFD computation in the inlet duct control section, coincide with the experimental data with a sufficiently high accuracy for all investigated operating conditions,<\/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_35801117.pdf\" data-type=\"link\" data-id=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2023\/10\/hisst-2018_35801117.pdf\">Read the full paper &gt; <\/a><\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>Novogorodtsev E.V.<\/b><br \/>\nDOI Number XXX-YYY-ZZZ<\/p>\n<p>Conference Number HiSST 2018_35801117<\/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":[900,434,901,899],"class_list":["post-13541","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-convergent-air-intake","tag-hisst-2018","tag-root-mean-square-parameter-of-the-total-pressure-pulsations-intensity","tag-total-distortion-parameter","category-996","category-994","category-198","category-1002","description-off"],"_links":{"self":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/13541","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=13541"}],"version-history":[{"count":3,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/13541\/revisions"}],"predecessor-version":[{"id":16527,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/13541\/revisions\/16527"}],"wp:attachment":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/media?parent=13541"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/categories?post=13541"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/tags?post=13541"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}