{"id":22844,"date":"2025-10-24T10:54:44","date_gmt":"2025-10-24T10:54:44","guid":{"rendered":"https:\/\/aerospacerepository.org\/?p=22844"},"modified":"2025-10-24T10:54:45","modified_gmt":"2025-10-24T10:54:45","slug":"parametric-study-of-classical-instabilities-in-three-dimensional-hypersonic-flows","status":"publish","type":"post","link":"https:\/\/aerospacerepository.org\/index.php\/2025\/10\/24\/parametric-study-of-classical-instabilities-in-three-dimensional-hypersonic-flows\/","title":{"rendered":"Parametric study of classical instabilities in three-dimensional hypersonic flows"},"content":{"rendered":"\n<p><strong>Thomas ZIELINSKI, Jos\u00e9 CARDESA, Guillaume BEGOU, Jean-Philippe BRAZIER, Laurent MUSCAT, Marina OLAZABAL-LOUM\u00c9<\/strong><\/p>\n\n\n\n<p><strong>DOI Number: N\/A<\/strong><\/p>\n\n\n\n<p><strong>Conference number: HiSST-2025-174<\/strong><\/p>\n\n\n\n<p>Boundary layer transition is of particular interest in the prediction of the aerodynamic performances and maneuverability of a given hypersonic vehicle. However, it has been found to be highly sensitive to flow parameters such as the Mach number, unit Reynolds number, cross-flow effects and wall temperature. Besides, from a numerical point of view, it is particularly difficult to obtain representative boundary-layer profiles to understand and then model these effects on the dominant instability modes. In this paper, a methodology relying on metric-based mesh adaptation has been validated and applied to address these issues. More specifically, the effects of the unit freestream Reynolds number, the wall temperature ratio Tw\/Tr and the angle of attack on various boundary layer profiles and the typical instability waves (cross-flow instability, first and second Mack modes) for a sharp 7-degree cone geometry are investigated. It has been observed that the increase in unit Reynolds number destabilizes all modes. Moreover, it was shown that the ratio Tw\/Tr has a drastic effect on these modes. Indeed, although the second Mack mode is strongly destabilized when lowering the Tw\/Tr ratio, the highly oblique modes behaved in the opposite fashion, being strongly destabilized with an increase of Tw\/Tr. Below Tw\/Tr \u2248 0.3, the first mode became completely stable and the crossflow mode was always unstable for all the chosen Tw\/Tr values. Finally, it has been found that the angle of attack significantly destabilized the crossflow instability by increasing the values of |wmax\/Ue| and the variation of edge quantities across the flowfield due to a stronger azimuthal pressure gradient induced by the curved bow shock.<\/p>\n\n\n\n<p><a href=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2025\/10\/HISST2025_174_paper.pdf\">Read the full paper here<\/a><\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>Thomas ZIELINSKI, Jos\u00e9 CARDESA, Guillaume BEGOU, Jean-Philippe BRAZIER, Laurent MUSCAT, Marina OLAZABAL-LOUM\u00c9<\/b><\/p>\n<p>DOI Number: N\/A<\/p>\n<p>Conference number: HiSST-2025-174<\/p>\n","protected":false},"author":2,"featured_media":0,"comment_status":"open","ping_status":"open","sticky":false,"template":"","format":"standard","meta":{"footnotes":""},"categories":[993,3367,3361],"tags":[3506,3600,440,3601],"class_list":["post-22844","post","type-post","status-publish","format-standard","hentry","category-events","category-high-speed-aerodynamics-and-aerothermodynamics-with-application-to-hypersonic-regimes","category-1-hisst-2025","tag-boundary-layer-transition-2","tag-flow-stability","tag-hypersonic","tag-three-dimensional-flows","category-993","category-3367","category-3361","description-off"],"_links":{"self":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/22844","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=22844"}],"version-history":[{"count":1,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/22844\/revisions"}],"predecessor-version":[{"id":22846,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/22844\/revisions\/22846"}],"wp:attachment":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/media?parent=22844"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/categories?post=22844"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/tags?post=22844"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}