Computational Investigation of Aerodynamic Characteristics for Elliptic UAVs’ Wing

Authors

  • Amaal Attiah Mechanical Power Engineering Department, Faculty of Engineering - Mattaria, Helwan University Cairo 11718, Egypt
  • Ibrahim Elbadawy Department of Mechanical Engineering, College of Engineering and Technology American University of the Middle East, Kuwait
  • Osama E. Mahmoud Mechanical Power Engineering Department, Faculty of Engineering - Mattaria, Helwan University Cairo 11718, Egypt

DOI:

https://doi.org/10.24203/ajet.v6i3.5391

Keywords:

UAV, Elliptic airfoil, Aerodynamics

Abstract

Unmanned Aerial Vehicles, UAVs, gained an important role in modern military and civilian applications. Developments in UAVs technology improve its performance and maneuverability with acceptable cost. Elliptic airfoil had been widely used in the development of Rotor/Wing subsonic aircraft. The present work aims to investigate the effect of various elliptic airfoil parameters, such as Reynolds number, angle of attack and airfoil thickness, on aerodynamic behavior using two-dimensional computational study. The computational results were validated by experimental results. Angles of attack was evaluated from 0° to 18° in order to analyze aerodynamic characteristics up to stall condition, while Reynolds number was evaluated at values of 1×10âµ, 3×105, 2×106, and 8×106, to cover the range of rotary and fixed wing flight conditions. Thickness ratio was ranged from 5% to 25% to include the UAVs airfoil thicknesses so that choice best thickness gets max lift to drag ratio. In addition, the thicknesses location was evaluated for a range of 30% to 70% to get suitable location gets max left to drag ratio. The ANSYS-Fluent software was used with Spalart-Allmaras turbulence model, and found that the maximum lift to drag ratio which improve the UAV capability in this study is at Re=2×106, angle of attack at 8°, max thickness ratio of (0.1chord) located at (0.3chord).

References

• Hossain, P. A. (2007). Lift analysis of an Aircraft model with and Without Winglet. International Conference on Mechanical Engineering, (ICME2007), Dhaka, Bangladesh..

• Hassan Muneel Syed, M. S. (2011). a Review of Swept and Blended Wing Body performance utilizing experimental, FE and aerodynamic techniques. www.arpapress.com.

• In Seong Hwang, S. Y. (2016). Structural design and analysis of elliptic cyclocopter rotor blades. National University, Korea 2Flight Vehicle Research Center, Korea.

• Introductory FLUENT notes. (2006).

• Keith, N. a. (2006). a Computational Study of the Flow Fields around Supersonic Airfoils and Subsonic Speeds.

• Kwon, K. a. (2005). Aerodynamic Characteristics of an Elliptic Airfoil at Low Reynolds Number. AIAA 2005-4762.

• Md. Fazlay Rabbey, E. A. (2013). Technical Development of Design & Fabrication of an Unmanned Aerial Vehicle. IOSR Journal of Mechanical and Civil Engineering (IOSR-JMCE).

• Michele Trancossi, C. B. (2015). Multifunctional unmanned reconnaissance aircraft for low speed and stol operations. SAE Technical Paper 2015-01-2465, doi:10.4271/2015-01-2465.

• Migita, S. A. (n.d.). Effects of low Reynolds numbers on the aerodynamics of micro air vehicles. Department of Mechanical Engineering University of Hawaii at Manoa Honolulu, HI 96822.

• Mohammad Salahuddin, M. O.-u.-R. (2013). a Report on Numerical Investigation of Wings: with and Without Winglet. International Journal of research in aeronautical and mechanical engineering, ISSN (online): 2321-3051. vol.1 I

• Pandya, S. A. (2001). Computation of External Aerodynamics for a Canard Rotor/Wing Aircraft. AIAA Paper 2001-0997,.

• R.I Ahmed, A. A. (2016). Aerodynamics and Flight Mechanics of MAV Based on Coanda Effect. Aerospace Science and Technology.

• Saharudin, M. F. (2016). Development of tilt-rotor unmanned aerial vehicle (UAV): material selection and structural analysis on wing design. IOP Conf. Series: Materials Science and Engineering 152, Selangor, Malaysia.

• Singh., S. a. (2012). Computational Fluid Dynamics Study of Fluid Flow and Aerodynamic Forces on an Airfoil. ISSN: 2278-0181.

• Tan Kar ZHEN, M. Z. (2011). Experimental and Numerical Investigation of the Effects of Passive Vortex Generators on Aludra UAV Performance. Chinese Journal of Aeronautics.

• Yang, H. H. (2008). An experimental study of the Laminar flow separation on a Low- Reynolds-Number airfoil. Department of Aerospace Engineering, Iowa State University, Ames, IA50011.

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Published

2018-08-19

How to Cite

Attiah, A., Elbadawy, I., & Mahmoud, O. E. (2018). Computational Investigation of Aerodynamic Characteristics for Elliptic UAVs’ Wing. Asian Journal of Engineering and Technology, 6(3). https://doi.org/10.24203/ajet.v6i3.5391

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