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Aerospace 2016, 3(3), 25; doi:10.3390/aerospace3030025

Effect of the Backward-Facing Step Location on the Aerodynamics of a Morphing Wing

Department of Aerospace Engineering, Ryerson University, Toronto, ON M5B 2K3, Canada
These authors contributed equally to this work.
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Academic Editor: Rafic Ajaj
Received: 13 June 2016 / Revised: 16 July 2016 / Accepted: 8 August 2016 / Published: 11 August 2016
(This article belongs to the Special Issue Adaptive/Smart Structures and Multifunctional Materials 2016)
View Full-Text   |   Download PDF [5215 KB, uploaded 11 August 2016]   |  

Abstract

Over the last decade, aircraft morphing technology has drawn a lot of attention in the aerospace community, because it is likely to improve the aerodynamic performance and the versatility of aircraft at different flight regimes. With the fast paced advancements in this field, a parallel stream of research is studying different materials and designs to develop reliable morphing skins. A promising candidate for a viable morphing skin is the sliding skin, where two or more rigid surfaces remain in contact and slide against each other during morphing. The overlapping between each two panels create a backward-facing step on the airfoil surface which has a critical effect on the aerodynamics of the wing. This paper presents a numerical study of the effect of employing a backward-facing step on the suction side of a National Advisory Committee for Aeronautics (NACA) 2412 airfoil at a high Reynolds number of 5.9 × 106. The effects of the step location on the lift coefficient, drag coefficient and critical angle of attack are studied to find a favorable location for the step along the chord-wise direction. Results showed that employing a step on the suction side of the NACA 2412 airfoil can adversely affect the aforementioned aerodynamic properties. A drop of 21.1% in value of the lift coefficient and an increase of 120.8% in the drag coefficient were observed in case of a step located at 25% of the chord length. However, these effects are mitigated by shifting the step location towards the trailing edge. Introducing a step on the airfoil caused the airfoil’s thickness to change, which in turn has affected the transition point of the viscous boundary layer from laminar to turbulent. The location of the step, prior or post the transition point, has a noteworthy effect on the pressure and shear stress distribution, and consequently on the values of the lift and drag coefficients. View Full-Text
Keywords: backward-facing step; aerodynamics; sliding morphing skin; step location; computational fluid dynamics backward-facing step; aerodynamics; sliding morphing skin; step location; computational fluid dynamics
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This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited. (CC BY 4.0).

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MDPI and ACS Style

Mishriky, F.; Walsh, P. Effect of the Backward-Facing Step Location on the Aerodynamics of a Morphing Wing. Aerospace 2016, 3, 25.

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