Numerical Optimization and Experimental Testing of a Morphing Wing with Aileron System

Koreanschi, Andreea; Gabor, Oliviu Şugar; Ayrault, Tristan; Botez, Ruxandra; Mamou, Mahmoud; Mébarki, Youssef

doi:10.2514/6.2016-1083

Cited by 15 publications

(11 citation statements)

References 26 publications

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“…The e n method is implemented for transition point detection [3]. Koreanschi et al used Xfoil for the evaluation of the base airfoil performance in their study that presented numerical optimization and experimental wind tunnel testing of a morphing wing tip equipped with an adaptable upper surface, and a rigid aileron [4]. Gabor et al used Xfoil in the high angle of attack ðαÞ optimization of a morphing airfoil as a function evaluator [5].…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Optimization of a UAV Wing subject to Weight, Geometric, Root Bending Moment, and Performance Constraints

Körpe

Kanat

2019

International Journal of Aerospace Engineering

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In this study, the optimization of a low-speed wing with functional constraints is discussed. The aerodynamic analysis tool developed by the coupling of the numerical nonlinear lifting-line method to Xfoil is used to obtain lift and drag coefficients of the baseline wing. The outcomes are compared with the results of the solver based on the nonlinear lifting-line theory implemented into XLFR5 and the transition shear stress transport model implemented into ANSYS-Fluent. The agreement between the results at the low and moderate angle of attack values is observed. The sequential quadratic programming algorithm of the MATLAB optimization toolbox is used for the solution of the constrained optimization problems. Three different optimization problems are solved. In the first problem, the maximization of C 3/2 L /C D is the objective function, while level flight condition at maximum C 3/2 L /C D is defined as a constraint. The functional constraints related to the wing weight, the wing planform area, and the root bending moment are added to the first optimization problem, and the second optimization problem is constructed. The third optimization problem is obtained by adding the level flight condition and the available power constraints at the maximum speed and the level flight condition at the minimum speed of the baseline unmanned air vehicle to the second problem. It is demonstrated that defining the root bending moment, the wing area, and the available power constraints in the aerodynamic optimization problems leads to more realistic wing planform and airfoil shapes.

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Section: Introductionmentioning

confidence: 99%

Aerodynamic Optimization of a UAV Wing subject to Weight, Geometric, Root Bending Moment, and Performance Constraints

Körpe

Kanat

2019

International Journal of Aerospace Engineering

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“…To reduce operating mistake the mesh was generated by ANSYS ICEM CFD software. The mesh considerate here ( Figure 6) is the same that was used for MDO 505 wing project [9], the wing is defined by 400 cells around the airfoil and 160 cells along the span. ANSYS Fluent is one of the most known software commercially available to compute aerodynamics coefficients.…”

Section: Computational Fluid Dynamics Methodsmentioning

confidence: 99%

“…The actuators change the airfoil shape during the flight by means of a PID controller [12][13][14]. [7,9,15]. The Morphing Wing concept presented in Figure 3 was successfully applied in the CRIAQ MDO 505 project.…”

Section: Application Of the Morphing Wing Concept On Uas-s4mentioning

confidence: 99%

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Morphing Wing Application on Hydra Technologies UAS-S4

Segui¹,

Gabor²,

Koreanschi³

et al. 2017

Modelling, Identification and Control

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This paper presents the aerodynamic results of a morphing wing study performed on the UAS S4 Éhecatl from Hydra Technologies. Only the cruise phase of the aircraft was considered (constant altitude and constant speed). The difference, from an aerodynamic point of view, between the morphing wing and the original wing was emphasized by computing and comparing their longitudinal aerodynamic coefficients (drag and lift). The computation of the aerodynamic characteristics was done using tornado with the Vortex Lattice Method.

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“…For a specific combination of angles of attack, speeds and aileron deflection angle, the mobile points were displaced with values between -3.5 mm and 3.5 mm during the optimization iteration process until it was achieved the objective of delaying the transition from laminar to turbulent flow. Further information on the aerodynamic optimization process and its results, obtained both numerically and experimentally, was presented by Koreanschi et al [34][35][36] and Sugar et al 37 . In order to maintain the structural integrity of the demonstrator, the aerodynamic optimization was constraint by geometry and skin deformation limitations.…”

Section: Presentation Of the Research Contextmentioning

confidence: 99%

Flutter Analysis of a Morphing Wing Technology Demonstrator: Numerical Simulation and Wind Tunnel Testinga

Koreanschi¹,

ben²,

Olivier³

et al. 2016

INCAS BULLETIN

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Numerical Optimization and Experimental Testing of a Morphing Wing with Aileron System

Cited by 15 publications

References 26 publications

Aerodynamic Optimization of a UAV Wing subject to Weight, Geometric, Root Bending Moment, and Performance Constraints

Aerodynamic Optimization of a UAV Wing subject to Weight, Geometric, Root Bending Moment, and Performance Constraints

Morphing Wing Application on Hydra Technologies UAS-S4

Flutter Analysis of a Morphing Wing Technology Demonstrator: Numerical Simulation and Wind Tunnel Testinga

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