Morphing wing optimization for steady level flight

Date

2017-11-01

Author

Korpe, Durmus S.
Özgen, Serkan

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This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

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This paper presents the basic results of the morphing wing planform optimization of an experimental unmanned air vehicle for minimum drag at steady level flight. The aerodynamic design tool that consists of the three-dimensional panel method, two-dimensional boundary layer solution and generalized reduced gradient method-based optimization is appropriate for fixed wing and morphing wing conceptual and preliminary design. The morphing concept is implemented into the solution with the geometric constraints of the wing planform and the airfoil shape design variables. The drag that is created by other components of the aircraft is calculated according to empirical formulas. Wing drag and aircraft drag comparisons between baseline wing (BASE), optimum fixed wing and morphing wing are discussed with the obtained planform and airfoil shapes.

Subject Keywords

Morphing wing, Panel method, Boundary layer flow, Optimization, Low-speed aerodynamics, Conceptual airplane design

URI

https://hdl.handle.net/11511/40805

Journal

PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING

DOI

https://doi.org/10.1177/0954410016662063

Collections

Department of Aerospace Engineering, Article

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Citation Formats

D. S. Korpe and S. Özgen, “Morphing wing optimization for steady level flight,” PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING, pp. 2317–2330, 2017, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/40805.