Advertisement

Structural and Modal Analyses of Naca 66-206 Aircraft Wing Model

  • Ismail Bogrekci
  • Pinar DemirciogluEmail author
  • H. Saygin Sucuoglu
  • Emrah Guven
  • Neslihan Demir
  • M. Numan Durakbasa
Conference paper
Part of the Lecture Notes in Mechanical Engineering book series (LNME)

Abstract

In this study, NACA 66-206 wing type was modelled and analysed to understand to mechanical behaviour under lift and weight forces. Structural and modal analyses were applied using Ansys Workbench Static Structural and Modal Analysis tools. Three different materials (aluminum 6061, carbon fiber and strong unidirectional epoxy glass) were selected for structure of the wings. The wings were created with three parts as airfoil, rib and spar. The affected forces were calculated and applied to the wings for three motion velocities as 10, 50 and 100 m/s. In the analyses; the lift forces were calculated by the buoyancy equation for the aircraft. The weight forces were also added to get more realistic results. The motion velocity and material effects to the structural strength of the wings were compared according to the results obtained from static and modal analyses. The maximum deformations were observed for the 100 m/s motion velocity with the values of 2.28 mm for aluminum, 0.16 mm for carbon fiber and 7.71 mm for epoxy glass. The similar effects of the motion velocity were found for the strains and equivalent stresses. It can be concluded from these results that it was better to manufacture the NACA 66-206 wings with the carbon fiber material as it had high natural frequency values and caused to lowest weight force.

Keywords

Lift and weight forces for aircraft wing Maximum deformation NACA 66-206 aircraft wing model Natural frequency Structural and modal analyses 

References

  1. 1.
    International Civil Aviation Organization (ICAO). Operation of Aircraft, Part I International Commercial Air Transport – Aeroplanes (Ninth Edition), Canada (2010)Google Scholar
  2. 2.
  3. 3.
    NASA: Four Forces on an Airplane (2019). https://www.grc.nasa.gov/www/k-12/airplane/forces.html
  4. 4.
    MIT: Theory of Flight (2019). http://web.mit.edu/16.00/www/aec/flight.html
  5. 5.
    Fielding, J.P.: Introduction to Aircraft Design. Cambridge Aerospace Series (1999)Google Scholar
  6. 6.
    Mohite, P.M.: Lecture Notes – Basic Aircraft Construction (2019). http://home.iitk.ac.in/~mohite/Basic_construction.pdf
  7. 7.
  8. 8.
  9. 9.
    Peruru, S.P., Abbisetti, S.B.: Design and finite element analysis of aircraft wing using ribs and spars. Int. Res. J. Eng. Technol. (IRJET) 04(i.06), 2133–2139 (2017)Google Scholar
  10. 10.
    Raid, S.Z.: Finite Element, Modal Testing and Modal Analysis of a Radial Flow Impeller. Iran. J. Sci. Technol. Trans. B, Eng. 29(B2), 157–169 (2005)Google Scholar
  11. 11.
    Abdelal, G.F., Abuelfoutouh, N., Gad, A.H.: Finite Element Analysis of Satellite Structures, Applications to Their Design, Manufacture and Testing. Springer Verlag, London (2013)CrossRefGoogle Scholar
  12. 12.
    Demirtas, A., Bayraktar, M.: Free vibration analysis of an aircraft wing by considering as a cantilever beam. Selcuk Univ. J. Eng. Sci. Tech. 7(1), 12–21 (2019)Google Scholar
  13. 13.
    Saran, V., Jayakumar, V., Bharathiraja, G.: Analysis of natural frequency for an aircraft wing structure under pre-stress condition. Int. J. Mech. Eng. Technol. (IJMET) 8(8), 1118–1123 (2017)Google Scholar
  14. 14.
  15. 15.
    Aerodynamic Lift, Drag and Moment Coefficients. https://aerotoolbox.net/lift-drag-moment-coefficient/

Copyright information

© Springer Nature Switzerland AG 2020

Authors and Affiliations

  • Ismail Bogrekci
    • 1
  • Pinar Demircioglu
    • 1
    Email author
  • H. Saygin Sucuoglu
    • 1
  • Emrah Guven
    • 1
  • Neslihan Demir
    • 1
  • M. Numan Durakbasa
    • 2
  1. 1.Mechanical Engineering DepartmentAydın Adnan Menderes UniversityAydınTurkey
  2. 2.Department of Industrial Metrology and Adaptronic SystemsVienna University of Technology (TU Vienna)ViennaAustria

Personalised recommendations