| Téléchargement | - Voir le manuscrit accepté : Boundary layer behaviour on a morphing airfoil: simulation and wind tunnel tests (PDF, 742 Kio)
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| Auteur | Rechercher : Sainmont, Corentin; Rechercher : Paraschivoiu, Ion; Rechercher : Coutu, Daniel; Rechercher : Brailovski, Vladimir; Rechercher : Laurendeau, Eric; Rechercher : Mamou, Mahmoud1; Rechercher : Mebarki, Youssef1; Rechercher : Khalid, Mahmood1 |
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| Affiliation | - Conseil national de recherches du Canada. Institut de recherche aérospatiale du CNRC
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| Format | Texte, Article |
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| Conférence | Canadian Aeronautics and Space Institute AERO '09 Conference Aerodynamics Symposium, May 5-7, 2009, Kanata, Ontario |
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| Résumé | This paper presents the boundary layer transitional flow behaviour past a morphing experimental wing. The objective of the present investigation is to reduce aerodynamic drag through laminar-turbulent transition location delay to promote large laminar region on the wing surface. The airfoil shape configurations of the adaptable part of the wing were optimized to extend the laminar flow on the upper surface of the airfoil. The optimizations were preformed with two different approaches. The classical approach uses a mathematical curve to model the flexible part. The multidisciplinary approach integrates the finite element model of the adaptable wing structure into the aerodynamic optimization process. The latter approach avoids the difficult task of reproducing the geometric representations of the airfoils, leading to the optimum performances offered by the morphing wing system. The optimizations are performed for various subsonic incompressible regimes using the computational fluid dynamics code Xfoil (Drela 2006) and the structural analysis software ANSYS coupled with a genetic optimization algorithm (Genial v1.1). Simulation and experimental results are presented and show that the morphing system is able to delay the transition location downstream by up to 30% of the chord length and to reduce the airfoil drag by up to 22%. Infra red maps and unsteady pressure frequency spectra measured on of the upper surface of the wing are also presented and show the laminar run extension. |
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| Date de publication | 2009 |
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| Dans | |
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| Langue | anglais |
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| Publications évaluées par des pairs | Oui |
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| Publication du CNRC | Cette publication n’est pas du CNRCCe sont des publications qui ont été rédigées par un auteur du CNRC, mais avant que celui-ci soit employé du CNRC. |
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| Numéro NPARC | 23001257 |
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| Exporter la notice | Exporter en format RIS |
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| Signaler une correction | Signaler une correction (s'ouvre dans un nouvel onglet) |
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| Identificateur de l’enregistrement | 2c4c7828-10d2-465e-95be-467d03da751a |
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| Enregistrement créé | 2017-01-12 |
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| Enregistrement modifié | 2020-08-11 |
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