{"status":"ok","message-type":"work","message-version":"1.0.0","message":{"indexed":{"date-parts":[[2025,12,15]],"date-time":"2025-12-15T17:10:31Z","timestamp":1765818631778,"version":"3.48.0"},"reference-count":25,"publisher":"American Institute of Aeronautics and Astronautics (AIAA)","funder":[{"DOI":"10.13039\/501100001871","name":"Funda\u00c3\u00a7\u00c3\u00a3o para a Ci\u00c3\u00aancia e a Tecnologia","doi-asserted-by":"publisher","award":["LA\/P\/0079\/2020"],"award-info":[{"award-number":["LA\/P\/0079\/2020"]}],"id":[{"id":"10.13039\/501100001871","id-type":"DOI","asserted-by":"publisher"}]},{"DOI":"10.13039\/501100001871","name":"Funda\u00c3\u00a7\u00c3\u00a3o para a Ci\u00c3\u00aancia e a Tecnologia","doi-asserted-by":"publisher","award":["UIDB\/50022\/2020"],"award-info":[{"award-number":["UIDB\/50022\/2020"]}],"id":[{"id":"10.13039\/501100001871","id-type":"DOI","asserted-by":"publisher"}]},{"DOI":"10.13039\/501100001871","name":"Funda\u00c3\u00a7\u00c3\u00a3o para a Ci\u00c3\u00aancia e a Tecnologia","doi-asserted-by":"publisher","award":["UIDP\/50022\/2020"],"award-info":[{"award-number":["UIDP\/50022\/2020"]}],"id":[{"id":"10.13039\/501100001871","id-type":"DOI","asserted-by":"publisher"}]}],"content-domain":{"domain":["arc.aiaa.org"],"crossmark-restriction":true},"short-container-title":["Journal of Aircraft"],"abstract":"<jats:p>This study investigates the aerodynamic characteristics of the Prandtl-D wing that incorporates twist to achieve Prandtl\u2019s bell-shaped lift distribution (BSLD) as a solution for minimizing induced drag. Prandtl\u2019s theoretical claims indicate that the bell spanload reduces induced drag when compared with its more popular counterpart, the elliptical lift distribution. Such enhancements in lift performance have been reasserted experimentally but are underexplored computationally. This investigation seeks to understand whether common CFD turbulence models are suitable for cross-validation of experimental BSLD research. Solutions for spanwise lift distribution, acquired in the steady-state Reynolds-averaged framework with Spalart\u2013Allmaras turbulence closure, are in close agreement with both theoretical and wind tunnel measurements. Analysis of stall and wingtip vortices provides further insight into the aircraft\u2019s enhanced controllability at high angles of attack.<\/jats:p>","DOI":"10.2514\/1.c038499","type":"journal-article","created":{"date-parts":[[2025,12,15]],"date-time":"2025-12-15T17:07:51Z","timestamp":1765818471000},"page":"1-9","update-policy":"https:\/\/doi.org\/10.2514\/aiaa_crossmarkpolicy","source":"Crossref","is-referenced-by-count":0,"title":["Numerical Analysis of the Prandtl-D Wing Using OpenFOAM"],"prefix":"10.2514","author":[{"ORCID":"https:\/\/orcid.org\/0009-0003-6272-7563","authenticated-orcid":false,"given":"Brian E.","family":"Santos","sequence":"first","affiliation":[{"name":"University of Coimbra"}]},{"ORCID":"https:\/\/orcid.org\/0000-0001-5043-9474","authenticated-orcid":false,"given":"Pedro M.","family":"Brito","sequence":"additional","affiliation":[{"name":"University of Coimbra"}]},{"ORCID":"https:\/\/orcid.org\/0000-0002-6056-0160","authenticated-orcid":false,"given":"Almerindo D.","family":"Ferreira","sequence":"additional","affiliation":[{"name":"University of Coimbra"}]}],"member":"1387","published-online":{"date-parts":[[2025,12,15]]},"reference":[{"issue":"11","key":"r1","first-page":"305","volume":"24","author":"Prandtl L.","year":"1933","journal-title":"Zeitschrift f\u00fcr Flugtechnik und Motorluftschiffahrt"},{"key":"r2","first-page":"40","volume-title":"Soaring","author":"Horten R.","year":"1981"},{"key":"r3","doi-asserted-by":"publisher","DOI":"10.2514\/6.2021-0826"},{"key":"r4","doi-asserted-by":"publisher","DOI":"10.2514\/6.2023-1979"},{"key":"r5","doi-asserted-by":"publisher","DOI":"10.3390\/aerospace9010013"},{"key":"r6","doi-asserted-by":"publisher","DOI":"10.2514\/6.2024-2114"},{"key":"r7","doi-asserted-by":"publisher","DOI":"10.2514\/1.C035027"},{"key":"r8","unstructured":"BowersA. 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