International Research Journal of Innovations in Engineering and Technology - IRJIET International Open Access, Monthly, Peer Reviewed, Reputed Journal ISSN (online): 2581-3048

Impact Factor (2025): 6.9

DOI Prefix: 10.47001/IRJIET

Analysis of Aerodynamics Load of a Flapping Wing by Vortex Lattice Method

Abstract

The aim of this study is to investigate the effect of changing the angle of attack and flapping angle on the aerodynamic characteristics of an unsymmetrical wing with the NACA 2412 profile. This work uses the Vortex Lattice Method. The results of this study show that increasing the flapping angle causes the pitching moment to decrease while induced drag and moment coefficient increase, meanwhile, the lift coefficient increases at positive angles of attack and then decreases at negative angles of attack. The pitching moment decreases with increasing angle of attack at positive flap angles, but this value increases at negative flap angles. Meanwhile, the induced drag decreases from an angle of attack -15° to a minimum at an angle of attack -5° and then increases. The moment coefficient increases with increasing angle of attack at positive flapping angles, but decreases at negative flapping angles. Meanwhile, the lift coefficient increases with increasing angle of attack.

Country : Indonesia

1 Ismoyo Haryanto2 Khoiri Rozi3 Berkah Fajar TK4 Alwahidil Zuhri

  1. Mechanical Engineering, Diponegoro University, Jl. Prof. H. Soedarto, SH, Tembalang, Semarang 50275, Indonesia
  2. Mechanical Engineering, Diponegoro University, Jl. Prof. H. Soedarto, SH, Tembalang, Semarang 50275, Indonesia
  3. Mechanical Engineering, Diponegoro University, Jl. Prof. H. Soedarto, SH, Tembalang, Semarang 50275, Indonesia
  4. Mechanical Engineering, Diponegoro University, Jl. Prof. H. Soedarto, SH, Tembalang, Semarang 50275, Indonesia

IRJIET, Volume 8, Issue 9, September 2024 pp. 297-301

doi.org/10.47001/IRJIET/2024.809036

Full Paper
Download

References

  1. A.J. Singh, S. Wala, S. H. Ladakhan, R. B. Sreesha, and S. M. Adinarayanappa, “Design and fabrication of shape memory alloy based 4D-printed actuator for FWMAV: A performance study,” Mater. Today Proc., no. xxxx, 2023.
  2. T. Ozaki and K. Hamaguchi, “Improved lift force of a resonant-driven flapping-wing micro aerial vehicle by suppressing wing–body and wing–wing vibration coupling,” Extrem. Mech. Lett., vol. 40, p. 100867, 2020.
  3. T. Q. Le, J. H. Ko, D. Byun, S. H. Park, and H. C. Park, “Effect of Chord Flexure on Aerodynamic Performanceof a Flapping Wing,” J. Bionic Eng., vol. 7, no. 1, pp. 87–94, 2010.
  4. W. He, X. Mu, L. Zhang, and Y. Zou, “Modeling and trajectory tracking control for flapping-wing micro aerial vehicles,” IEEE/CAA J. Autom. Sin., vol. 8, no. 1, pp. 148–156, 2021.
  5. T. WANG, L. LIU, J. LI, and L. ZENG, “Time-history performance optimization of flapping wing motion using a deep learning based prediction model,” Chinese J. Aeronaut., vol. 37, no. 5, pp. 317–331, 2024.
  6. M. Kiani et al., “A new bio-inspired flying concept: The quad-flapper,” AIAA Scitech 2019 Forum, no. January, pp. 1–12, 2019.
  7. M. F. Bin Abas, A. S. Bin Mohd Rafie, H. Bin Yusoff, and K. A. Bin Ahmad, “Flapping wing micro-aerial vehicle: Kinematics, membranes, and flapping mechanisms of ornithopter and insect flight,” Chinese J. Aeronaut., vol. 29, no. 5, pp. 1159–1177, 2016.
  8. F. Song, Y. Yan, and J. Sun, “Review of insect-inspired wing micro air vehicle,” Arthropod Struct. Dev., vol. 72, p. 101225, 2023.
  9. S. Xiao, K. Hu, B. Huang, H. Deng, and X. Ding, “A Review of Research on the Mechanical Design of Hoverable Flapping Wing Micro-Air Vehicles,” J. Bionic Eng., vol. 18, no. 6, pp. 1235–1254, 2021.
  10. D. Livescu, “Applied Computational Aerodynamics. A Modern Engineering Approach,” AIAA J., vol. 54, no. 11, pp. 3679–3680, 2016.
  11. J. D. Anderson, Fundamentals of Aerodynamics (6th edition), vol. 1984, no. 3. 2011.
  12. M. T. Nguyen, N. V. Nguyen, and M. T. Pham, “Aerodynamic Analysis of Aircraft Wing,” VNU J. Sci. Math. – Phys., vol. 31, no. 2, pp. 68–75, 2015.

Copyright @ 2026-2017 IRJIET. All Right Reserved.

Developed by Byzero Technologies