Aerodynamic analysis of a NACA 0015 airfoil with a variable-geometry morphing mechanism

Yemenici, Onur; Oruç, Emre

doi:10.30772/qjes.2026.169559.1907

	Aerodynamic analysis of a NACA 0015 airfoil with a variable-geometry morphing mechanism
Al-Qadisiyah Journal for Engineering Sciences
Articles in Press, Accepted Manuscript, Available Online from 24 May 2026 PDF (7.16 M)
Document Type: Research Paper
DOI: 10.30772/qjes.2026.169559.1907
Authors
Onur Yemenici^* ¹; Emre Oruç²
¹Department of Mechanical Engineering, Faculty of Engineering, University of Bursa Uluda˘g, Bursa, Turkiye.
²FORD OTOSAN, Sancaktepe Engineering Center, Engine Engineering-Hydrogen Cooling and FIE, Istanbul, Turkey.
Abstract
Advances in smart materials have made it possible to develop shape-changing wing concepts as alternatives to traditional high-lift systems. In this study, the aerodynamic effects of linear beam extension on a NACA 0015 wing profile with an initial beam length of 150 mm were numerically investigated. The linear actuation mechanism applied along the chord direction resulted in a reduction in the camber ratio. The aerodynamic performance of the conformable configurations was evaluated using CFD analyses conducted under low Reynolds number conditions and employing the k- SST turbulence model. The results indicate that chordwise deformation can improve aerodynamic performance under various operating conditions. This approach offers significant potential for enhancing maneuverability and reducing energy consumption in low-Reynolds-number aircraft, presenting a promising solution for future adaptive wing designs.
Keywords
Aerodynamic performance; Attack angle; CFD analysis; Chordwise morphing; NACA 0015 airfoil

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