Aerodynamic Performance Investigation of an Experimental Variable-Span Morphing Wing Model

Document Type : Original Article

Authors

• abbas tarabi ¹
• sajjad gasemloo ²
• mahmoud mani ²

¹ دانشگاه مالک اشتر

² امیر کبیر

10.22067/fum-mech.v27i1.38491

Abstract

In this paper, the implementation of the variable-span Morphing wing(VSMW) on the wings of a UAV to achiev the optimal performance for various flight regimes is studied in wind tunnels. For the implementation of this plan, a morphing wing with its related mechanism is designed, built and tested. Tests were carried out at a low- speed wind tunnel with speeds of 35, 60 and 80 m/s in the range of Reynolds Number between 250×〖10〗^3 to 620×〖10〗^3. For the implementation of the morphing wing plan, the maximum deviation of wing span relative to Basewing (BW) is 38 percent and change of aspect ratio is 74% percent. Experimental results showed the improved aerodynamic properties of VSMW compared to BW. These improvements are in the form of reduction of induced drag, thrust required and increasing of lift coefficient, aerodynamic efficiency, endurance and rang. According to the results, endurance and range for VSMW comparison to BW, respectively 17 and 5 percent increased. The experimental studies show that the maximum aerodynamic efficiency of the wing model occurs at 4 degree angle of attack with the maximum value being 14.8 for the base wing, 16.3 for the morphing wing with 50 percent (5 cm) extension in wing span, and 17.4 % for the morphing wing with 100 percent (10 cm) span extension. This research also shows how VSMW can be used as an alternative method of roll control instead of the regular method (i.e. using aileron control surfaces) as it provides more roll control power than the regular method.

Keywords

• Morphing Wing
• Variable Span
• wind tunnel
• Range and Endurance
• Aerodynamic Coefficient

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