{"status":"ok","message-type":"work","message-version":"1.0.0","message":{"indexed":{"date-parts":[[2026,5,4]],"date-time":"2026-05-04T00:21:57Z","timestamp":1777854117720,"version":"3.51.4"},"reference-count":8,"publisher":"SAGE Publications","issue":"15","license":[{"start":{"date-parts":[[2020,6,30]],"date-time":"2020-06-30T00:00:00Z","timestamp":1593475200000},"content-version":"tdm","delay-in-days":0,"URL":"https:\/\/journals.sagepub.com\/page\/policies\/text-and-data-mining-license"}],"content-domain":{"domain":["journals.sagepub.com"],"crossmark-restriction":true},"short-container-title":["Journal of Intelligent Material Systems and Structures"],"published-print":{"date-parts":[[2020,9]]},"abstract":"<jats:p>The dawn of research on shock and boundary layer interaction control dates back to the 1970s, when humped transonic aerofoils were first studied as a means to improve the performance of supercritical aerofoil technology at off-design conditions. Since then, shock control bumps have been found to be promising devices for such kind of flow control. They have a smearing effect on the shock wave structure achieved through isentropic pre-compression of the flow upstream of the main shock and can significantly lower wave drag without incurring unacceptable viscous losses. However, their performance is strongly dependent on a set of geometrical parameters which must be adjusted according to the ever-changing flight conditions. A concept for an adaptive shock control bump is therefore presented. The proposed actuation mechanism aims at a compact, lightweight and simple structure which could be integrated into the spoiler region of near-future aircraft without major design changes required. Numerical optimization of a simplified analytical model of the structure is used to investigate the shock control bump adaptation to various aerodynamic target shapes. Compromises between geometrical conformity and both structural and actuation related requirements are studied. Furthermore, an outlook is given on design issues related to three-dimensional effects on a finite span shock control bump.<\/jats:p>","DOI":"10.1177\/1045389x20932214","type":"journal-article","created":{"date-parts":[[2020,7,1]],"date-time":"2020-07-01T02:05:55Z","timestamp":1593569155000},"page":"1821-1837","update-policy":"https:\/\/doi.org\/10.1177\/sage-journals-update-policy","source":"Crossref","is-referenced-by-count":2,"title":["Morphing of an adaptive shock control bump using pressurized chambers"],"prefix":"10.1177","volume":"31","author":[{"given":"Nuno","family":"Alves de Sousa","sequence":"first","affiliation":[{"name":"Instituto Superior T\u00e9cnico, Universidade de Lisboa, Lisbon, Portugal"}]},{"given":"Markus","family":"Kintscher","sequence":"additional","affiliation":[{"name":"Deutsches Zentrum f\u00fcr Luft- und Raumfahrt, Institut f\u00fcr Faserverbundleichtbau und Adaptronik, Braunschweig, Germany"}]},{"ORCID":"https:\/\/orcid.org\/0000-0001-6498-2996","authenticated-orcid":false,"given":"Afzal","family":"Suleman","sequence":"additional","affiliation":[{"name":"University of Victoria, Victoria, BC, Canada"}]}],"member":"179","published-online":{"date-parts":[[2020,6,30]]},"reference":[{"key":"bibr1-1045389X20932214","first-page":"175","volume-title":"Proceedings 1st European forum on laminar flow technology","author":"Ashill P","year":"1992"},{"key":"bibr2-1045389X20932214","doi-asserted-by":"publisher","DOI":"10.1088\/0964-1726\/9\/2\/303"},{"key":"bibr3-1045389X20932214","doi-asserted-by":"publisher","DOI":"10.1007\/978-94-011-4199-4_8"},{"key":"bibr4-1045389X20932214","doi-asserted-by":"publisher","DOI":"10.1137\/S1052623496303470"},{"key":"bibr5-1045389X20932214","first-page":"1","volume-title":"CSEI2012 Confer\u00eancia Nacional sobre Computa\u00e7\u00e3o Simb\u00f3lica no Ensino e na Investiga\u00e7\u00e3o","author":"Policarpo H","year":"2012"},{"key":"bibr6-1045389X20932214","unstructured":"Smith JW, Lock WP, Payne GA (1992) Variable-camber systems integration and operational performance of the AFTI\/F-111 mission adaptive wing. In: NASA technical memorandum 4370. 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