{"id":17864,"date":"2024-08-16T08:07:43","date_gmt":"2024-08-16T08:07:43","guid":{"rendered":"https:\/\/aerospacerepository.org\/?p=17864"},"modified":"2024-08-16T08:07:44","modified_gmt":"2024-08-16T08:07:44","slug":"experimental-assessment-of-the-flutter-stability-of-a-laminar-airfoil-in-transonic-flow","status":"publish","type":"post","link":"https:\/\/aerospacerepository.org\/index.php\/2024\/08\/16\/experimental-assessment-of-the-flutter-stability-of-a-laminar-airfoil-in-transonic-flow\/","title":{"rendered":"EXPERIMENTAL ASSESSMENT OF THE FLUTTER STABILITY OF A LAMINAR AIRFOIL IN TRANSONIC FLOW"},"content":{"rendered":"\n<p><strong>Anne Hebler<\/strong><\/p>\n\n\n\n<p><strong>DOI Number: N\/A<\/strong><\/p>\n\n\n\n<p><strong>Conference number: IFASD-2017-089<\/strong><\/p>\n\n\n\n<p>First results of a \ufb02utter experiment in transonic \ufb02ow are presented. A wind tunnel model with the laminar CAST 10-2 airfoil was mounted elastically with heave and pitch degrees of freedom in the Transonic Wind Tunnel Goettingen. Laser triangulators and acceleration sensors were used to record the motion of the model. Measurements were taken with free and \ufb01xed boundary layer transition in a Mach number range of 0.5 \u2264 M a \u2264 0.85 and for chord Reynolds numbers of 1.0 \u00b7 106 \u2264 Rec \u2264 3.5 \u00b7 106. For free transition \ufb02utter and limit cycle oscillations occurred both when the model degrees of freedom were structurally coupled and when the degrees of freedom were only aerodynamically coupled. However when the boundary layer transition was \ufb01xed at 7.5% chord, \ufb02utter occured only in the case of structurally coupled degrees of freedom.<\/p>\n\n\n\n<p><a href=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2024\/08\/IFASD-2017-089.pdf\">Read the full paper here<\/a><\/p>\n\n\n\n<p><\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>Anne Hebler<b\/><\/p>\n<p>DOI Number: N\/A<\/p>\n<p>Conference number: IFASD-2017-089<\/p>\n","protected":false},"author":2,"featured_media":0,"comment_status":"open","ping_status":"open","sticky":false,"template":"","format":"standard","meta":{"footnotes":""},"categories":[993,1953,1965],"tags":[2119,438,2036,2117,2118],"class_list":["post-17864","post","type-post","status-publish","format-standard","hentry","category-events","category-ifasd-2017","category-wind-tunnel-and-flight-testing","tag-aeroelastic-stability","tag-experiment","tag-flutter-boundary","tag-laminar-airfoil","tag-transonic-flow-2","category-993","category-1953","category-1965","description-off"],"_links":{"self":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/17864","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=17864"}],"version-history":[{"count":1,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/17864\/revisions"}],"predecessor-version":[{"id":17866,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/17864\/revisions\/17866"}],"wp:attachment":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/media?parent=17864"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/categories?post=17864"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/tags?post=17864"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}