Analysis and optimization of morphing wing aerodynamics

• Published in: Aircraft engineering 2019-03, Vol.91 (3), p.538-546
• Main Authors: Klimczyk, Witold Artur, Goraj, Zdobyslaw Jan
• Format: Article
• Language: English
• Subjects: Aerodynamics; Aircraft; Design; Design optimization; Efficiency; Feasibility studies; Geometry; Morphing; Optimization; Parameter sensitivity; Parameterization; Pressure distribution; Response surface methodology; Three dimensional models; Trailing edges; Two dimensional analysis; Two dimensional models; Unmanned aerial vehicles
• ISSN: 1748-8842; 1758-4213
• DOI: 10.1108/AEAT-12-2017-0289

Purpose The purpose of this paper is to present a method for analysis and optimization of morphing wing. Moreover, a numerical advantage of morphing airfoil wing, typically assessed in simplified two-dimensional analysis is found using higher fidelity methods. Design/methodology/approach Because of multi-point nature of morphing wing optimization, an approach for optimization by analysis is presented. Starting from naïve parametrization, multi-fidelity aerodynamic data are used to construct response surface model. From the model, many significant information are extracted related to parameters effect on objective; hence, design sensitivity and, ultimately, optimal solution can be found. Findings The method was tested on benchmark problem, with some easy-to-predict results. All of them were confirmed, along with additional information on morphing trailing edge wings. It was found that wing with morphing trailing edge has around 10 per cent lower drag for the same lift requirement when compared to conventional design. Practical implications It is demonstrated that providing a smooth surface on wing gives substantial improvement in multi-purpose aircrafts. Details on how this is achieved are described. The metodology and results presented in current paper can be used in further development of morphing wing. Originality/value Most of literature describing morphing airfoil design, optimization or calculations, performs only 2D analysis. Furthermore, the comparison is often based on low-fidelity aerodynamic models. This paper uses 3D, multi-fidelity aerodynamic models. The results confirm that this approach reveals information unavailable with simplified models.