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Experimental and Numerical Study of Variable-Span-sweep Morphing Wing on the Aerodynamic Characteristics of UAV

A. Tarabi

¹

S. Gasemloo

^2*

, M. Mani

³

1- PhD student, Aerospace Eng., Aerospace Research Institute, Maleke-Ashtar University of Technology, Tehran, Iran 2- Aerospace Eng. Complex, Maleke-Ashtar University of Technology, Tehran, Iran

3-Prof., Aerospace Eng. Dep’t., Amirkabir University of Technology, Tehran, Iran

*P.O. B 441315875 Tehran, Iran. sghasemloo@aut.ac.ir

A RTICLE I NFORMATION A BSTRACT

Original Research Paper Received 16 December 2014 Accepted 19 January 2015 Available Online 24 January 201

In this research, experiment and computational fluid dynamics (CFD) are used to assess the performance of UAV with variable-span and sweep morphing wing under low speed conditions.

Both wing area and aspect ratio are changed due to variations in span and sweep, whereas structure of the variable-span and sweep morphing wing remains constant. In this study, the numerical results of Fluent software and experimental data are presented. Results are achieved under low wind speed (50, 60 and 70 m/s). In this case, full extension represents 30% (10 cm) increase in wing span and 36% (12 deg.) in sweep angle relative to the original wing, with no extension. The results of this study show that the morphing wing is capable to improved aerodynamic efficiency, increased both range and endurance, reduced induced drag and in general reduced thrust required. According to experimental and numerical results, the use of morphing wing can increase the range by 13.6% and 13.5%, also, endurance of the vehicle by approximately 8.855 and 8.17%, respectively. The results of this study show that the maximum value of lift-to-drag ratio occurred at degrees angle of attack and speed of 70m/s. These results demonstrate that the use of morphing wing improve the lift-to-drag ratio b 10%

compared to original wing. Finally, the numerical simulations are compared and show good agreement with the experimental results. This research also showed how morphing concept can be used as an alternative method for roll control instead of the traditional method of roll control (Aileron control surfaces).

Keywords:

Morphing Wing Variable Span and Sweep Numerical Method Wind tunnel

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