Skip to main content
SpringerLink
Log in

Numerical Study of a Transonic Aircraft Wing for the Prediction of Flutter Failure

  • Technical Article---Peer-Reviewed
  • Published:
Journal of Failure Analysis and Prevention Aims and scope Submit manuscript

Abstract

In the present paper, computational analysis has been carried out to assess the coupled fluid–structure interaction using NASTRAN finite element approach. A straight swept wing of aluminum material is studied at transonic zone. Analysis has been carried out to find the natural frequency by fluid–structure interaction, then adopting its natural frequency to calculate the reduced frequency for analyzing the flutter effectiveness. A typical case study of plate has been carried out for better understanding the flutter which was then adopted for the swept wing. A fluid–structure interaction phenomenon provides an additional energy to the moving object in terms of frequency in transonic zone. In this speed zone, the divergence speed results a drag that leads to the object to be in a stronger twisting mode resulting in catastrophic failure of the aircraft. The study has defined the flutter boundary of the wing in terms of velocity and frequency which will be very useful in preventing the flutter failure of the aircraft wing through appropriate design improvement or through restriction operational regime.

This is a preview of subscription content, log in via an institution to check access.

Access this article

Log in via an institution

Price excludes VAT (USA)
Tax calculation will be finalised during checkout.

Instant access to the full article PDF.

Institutional subscriptions

Fig. 1
Fig. 2
Fig. 3
Fig. 4
Fig. 5
Fig. 6
Fig. 7
Fig. 8
Fig. 9
Fig. 10
Fig. 11
Fig. 12
Fig. 13
Fig. 14
Fig. 15
Fig. 16
Fig. 17
Fig. 18

Similar content being viewed by others

References

  1. H.J.-P. Morand, O. Roger, Fluid Structure Interaction (Wiley, Hoboken, 1995)

    Google Scholar 

  2. L.C. Freudinger, Flutter Clearance of the F-18 High-Angle-of-Attack Research Vehicle with Experimental Wingtip Instrumentation Pods (NASA Dryden Flight Research Center, Edwards, 1989)

    Google Scholar 

  3. C.E. Lemley, Design Criteria for the Prediction and Prevention of Panel Flutter, vols. I and II, Air Force Flight Dynamics Laboratory, Write-Patternson Air Force Base, Ohio, AFFDL-TR-67-140 (1968)

  4. S.J. Pollock et al., Evaluation of methods for prediction and prevention of wing/store flutter. J. Aircr. 19(6), 492–498 (1982)

    Article  Google Scholar 

  5. E.M. Lee-Rausch, J.T. Batina, Wing flutter boundary prediction using unsteady Euler aerodynamic method. J. Aircr. 32(2), 416–422 (1995)

    Article  Google Scholar 

  6. F. Liu et al., Calculation of wing flutter by a coupled fluid–structure method. J. Aircr. 38(2), 334–342 (2001)

    Article  Google Scholar 

  7. C. Grandmont, Y. Maday, Existence for an unsteady fluid–structure interaction problem. ESAIM 34(3), 609–636 (2000)

    Article  Google Scholar 

  8. J. Zeng et al., Ground Vibration Test Identified Structure Model for Flutter Envelope Prediction. AIAA Atmospheric Flight Mechanics Conference 2012

  9. W. Chajec, Flutter calculation based on GVT-results and theoretical mass model. Aviation 13(4), 122–129 (2009)

    Article  Google Scholar 

  10. A.C. Pankaj et al., Aircraft flutter prediction using experimental modal parameters. Aircr. Eng. Aerosp. Technol. 85(2), 87–96 (2013)

    Article  Google Scholar 

  11. E. Lee-Rausch, J.T. Baitina, Wing flutter computations using an aerodynamic model based on the Navier–Stokes equations. J. Aircr. 33(6), 1139–1147 (1996)

    Article  Google Scholar 

  12. H.J. Cunningham, J.T. Batina, R.M. Bennett, Modern wing flutter analysis by computational fluid dynamics methods. J. Aircr. 25(10), 962–968 (1988)

    Article  Google Scholar 

  13. A.S.F. Wong, H.M. Tsai, Calculation of Wing Flutter by a Coupled CFD-CSD Method. 38th Aerospace Sciences Meeting and Exhibit, Aerospace Sciences Meetings (2000)

  14. P. Le Tallec, M. Jean, Fluid structure interaction with large structural displacements. Comput. Methods Appl. Mech. Eng. 190(24), 3039–3067 (2001)

    Article  Google Scholar 

  15. C. Pak, L. Shun-fat, Reduced Uncertainties in the Flutter Analysis of the Aerostructures Test Wing. 27th International Congress of the Aeronautical Sciences, 19–24 September 2010, Nice, France (2010)

  16. S. Raja et al., Flutter control of a composite plate with piezoelectric multilayered actuators. Aerosp. Sci. Technol. 10(5), 435–441 (2006)

    Article  Google Scholar 

  17. J. Heeg, An analytical and experimental investigation of flutter suppression via piezoelectric actuation (National Aeronautics and Space Administration, Langley Research Center, Hampton, 1992)

    Book  Google Scholar 

  18. P. Marzocca, L. Librescu, W.A. Silva, Flutter, post-flutter, and control of a supersonic wing section. J. Guid. Control Dyn. 25(5), 962–970 (2002)

    Article  Google Scholar 

Download references

Author information

Authors and Affiliations

  1. Jain University International Institute for Aerospace Engineering and Management, Bangalore, Karnataka, India

    Indrajeet Singh & P. S. Aswatha Narayana

  2. Regional Center for Military Airworthiness (Engines), Bangalore, Karnataka, India

    R. K. Mishra

Authors
  1. Indrajeet Singh
    View author publications

    You can also search for this author in PubMed Google Scholar

  2. R. K. Mishra
    View author publications

    You can also search for this author in PubMed Google Scholar

  3. P. S. Aswatha Narayana
    View author publications

    You can also search for this author in PubMed Google Scholar

Corresponding author

Correspondence to R. K. Mishra.

Rights and permissions

Reprints and permissions

About this article

Check for updates. Verify currency and authenticity via CrossMark

Cite this article

Singh, I., Mishra, R.K. & Aswatha Narayana, P.S. Numerical Study of a Transonic Aircraft Wing for the Prediction of Flutter Failure. J Fail. Anal. and Preven. 17, 107–119 (2017). https://doi.org/10.1007/s11668-016-0209-8

Download citation

  • Received:

  • Published:

  • Issue Date:

  • DOI: https://doi.org/10.1007/s11668-016-0209-8

Keywords

Search

Navigation