Comparison and analyses of a variable span-morphing of the tapered wing with a varying sweep angle

• Published in: Aeronautical journal Vol. 124; no. 1278; pp. 1146 - 1169
• Main Authors: Elelwi, M., Kuitche, M.A., Botez, R.M., Dao, T.M.
• Format: Journal Article
• Language: English
• Published: Cambridge, UK Cambridge University Press 01.08.2020
• Subjects: Aerodynamic characteristics; Aerodynamics; Aircraft; Aircraft configurations; Airfoils; Comparative studies; Configuration management; Design; Energy efficiency; Influence; Morphing; Rolling motion; Sea level; Studies; Sweep angle; Three dimensional flow; Two dimensional analysis; Unmanned aerial vehicles; Velocity; Wing design; aerodynamic analyses; aerodynamic performance; UAV design; variable span morphing of the tapered wing
• ISSN: 0001-9240; 2059-6464
• DOI: 10.1017/aer.2020.19

This work presents a comparative study of design and development, in addition, of analyses of variable span morphing of the tapered wing (VSMTW) for the unmanned aerial vehicle (UAV). The proposed concept consists in the sliding of the inner section into the fixed part along the wing with varying the angle of the inner section inside the fixed part (parallel with the leading edge and the moving-wing axis is coincident to the fixed-wing axis) within two configurations. The wing design is based on a NACA 4412 aerofoil with the root chord of 0.675m and the tip chord of 0.367m for the fixed segment and 0.320m for the moving segment. Morphing wing analysis occurs at three selected locations that have been specified for extending and modifying span length by (25%, 50%, and 75%) of its original length to fulfill various flight mission requirements. The main objective of this paper is to compare the aerodynamic characteristics for several span lengths and sweep angles and to find their most efficient combinations. The wing is optimised for different velocities during all phases of flight (min speed, loiter, cruise, and max speed) which are 17, 34, 51, and 68m/s, respectively. The analyses are performed by computing forces (drag and lift) and moments at various altitudes, such as at the sea level, at 5,000 and 10,000ft. Two-dimensional aerodynamic analyses are carried out using XFLR5 code, and the ANSYS Fluent solver is used for investigating the flow field on the three-dimensional wing structure. It has been observed that a variable span morphing of tapered wing technology with a variable sweep angle can deliver up to 32.93% improved aerodynamic efficiency. This concept design can also be used for the aircraft roll motion technique instead of conventional control devices. Furthermore, the range flight mission increases up to 46.89% when the wing is placed at its full length compared to an original position. Finally, it has been concluded from this study that the wing design is more sensitive to the changing angle of the inner section and more efficient in terms of aerodynamic characteristics.