Lift-to-drag ratio and laminar flow control of a morphing laminar wing in a wind tunnel

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  1. Obtenir@CNRC : Lift-to-drag ratio and laminar flow control of a morphing laminar wing in a wind tunnel (Ouvre dans une nouvelle fenêtre)
DOITrouver le DOI : http://doi.org/10.1088/0964-1726/20/3/035019
AuteurRechercher : ; Rechercher : ; Rechercher : ; Rechercher : ; Rechercher : ; Rechercher :
TypeArticle
Titre de la revueSmart Materials and Structures
ISSN0964-1726
Volume20
Numéro3
Numéro d'article35019
SujetAerodynamic performance; Closed loop controllers; Closed-loop; Closed-loop control; Control strategies; Cruise flight; Flow condition; Hard-ware-in-the-loop; Infra-red cameras; Lift-to-drag ratio; Morphing; Numerical optimizations; Open loop control; Open loops; Shape memory alloy actuators; Unactuated; Upper surface; Wing profiles; Cameras; Closed loop control systems; Drag; Laminar flow; Lift; Mach number; Structural optimization; Synthetic apertures; Temperature indicating cameras; Wind tunnels; Lift drag ratio
RésuméA new hardware-in-the-loop control strategy to enhance the aerodynamic performance of a two-dimensional morphing laminar wing prototype was developed and tested. The testing was performed in a wind tunnel under cruise flight flow conditions: Mach number ranging from 0.2 to 0.3 and angle of attack from - 1° to 0.5°. For each set of flow conditions, the shape of the upper surface of the wing was modified using two independent shape memory alloy actuators. The wing shape was morphed in two sequential steps. The initial morphed shape was controlled using open-loop architecture and the results of an anterior aero-structural numerical optimization study. The final morphed shape was closed-loop controlled using either the wind tunnel balance or an infrared camera as hardware-in-the-loop to give an instantaneous lift-to-drag ratio (L/D) or a laminar flow extension (x tr/c) over the upper surface of the prototype. In respect to the aerodynamic performance of the unactuated wing profile, the L/D gain varies from 10.6 to 15% for the closed-loop control strategy compared to 10.0 to 13.7% for the open-loop control strategy. Laminar flow extension gains, Δx tr/c, measured by infrared camera, were situated in the 29-33% range for both control strategies. However, the results obtained showed that the closed-loop controller could be hindered by the noise of the hardware-in-the-loop signal. © 2011 IOP Publishing Ltd.
Date de publication
Langueanglais
AffiliationConseil national de recherches Canada (CNRC-NRC); Aérospatiale (AERO-AERO)
Publications évaluées par des pairsOui
Numéro NPARC21271256
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Identificateur de l’enregistrement04a55d15-a94a-4734-95e0-9909da32fa7f
Enregistrement créé2014-03-24
Enregistrement modifié2016-05-09
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