Journal of Failure Analysis and Prevention

, Volume 17, Issue 5, pp 948–954 | Cite as

Finite Element Analysis of an Aircraft Wing Leading Edge Made of GLARE Material for Structural Integrity

  • Balachandra P. Shetty
  • Sudheer Reddy
  • R. K. Mishra
Technical Article---Peer-Reviewed


The present paper characterizes the structure of 3D model of an aircraft wing leading edge of a passenger aircraft considering GLARE laminates as one of the candidate materials through finite element analysis. The investigation is carried out on different types of GLARE configurations and the results of finite element analysis are well compared analytically with benchmark tests to demonstrate the performance of the modeling technique adopted. The GLARE laminate materials are found suitable for their application in the wing leading edge with some reservation on GLARE 3/2 and GLARE 4/3 for Al alloy 2024-T3 thickness, between 0.2 and 0.4 mm. The finite element approach is able to predict the mechanical behavior of structural elements fast enough so that the results can be incorporated into normal design iteration processes.


GLARE Laminate Wing leading edge Failure analysis Finite element method 


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Copyright information

© ASM International 2017

Authors and Affiliations

  • Balachandra P. Shetty
    • 1
  • Sudheer Reddy
    • 1
  • R. K. Mishra
    • 2
  1. 1.Nitte Meenakshi Institute of TechnologyBangaloreIndia
  2. 2.Regional Center for Military AirworthinessBangaloreIndia

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