Numerical and Experimental Investigations of Cantilever Rectangular Plate Structure on Subsonic Flutter

Authors: Mevlüt Burak Dalmış, Kemal Yaman

Abstract:

In this study, flutter characteristics of cantilever rectangular plate structure under incompressible flow regime are investigated by comparing the results of commercial flutter analysis program ZAERO^© with wind tunnel tests conducted in Ankara Wind Tunnel (ART). A rectangular polycarbonate (PC) plate, 5x125x1000 mm in dimensions, is used for both numerical and experimental investigations. Analysis and test results are very compatible with each other. A comparison between two different solution methods (g and k-method) of ZAERO^© is also done. It is seen that, k-method gives closer result than the other one. However, g-method results are on conservative side and it is better to use conservative results namely g-method results. Even if the modal analysis results are used for the flutter analysis for this simple structure, a modal test should be conducted in order to validate the modal analysis results to have accurate flutter analysis results for more complicated structures.

Keywords: Flutter, plate, subsonic flow, wind tunnel.

Digital Object Identifier (DOI): doi.org/10.5281/zenodo.1130455

References:

[1] M. H. Hansen. “Aeroelastic instability problems for wind turbines”, Wind Energy, 10(6), 2007.
[2] Y. C. Fung. “An Introduction to the Theory of Aeroelasticity”. Courier Dover Publications, May 2002.
[3] F.W. Lanchester, “Torsional vibration of the Tail of an Aeroplane”, Aeronaut. Research Com. R & M.276, part i, 1916.
[4] L. Bairstow, and A. Fage “Oscillations of the Tail Plane and Body of an Aeroplane in Flight”, Aeronaut. Research Com. R & M.276, part ii, 1916.
[5] H Blasius, “Über Schwingungserscheinungen an Einholmigen Unterflügeln”, Z. Flugtech. u. Motorluftschif. Vol. 16. pp. 39-42, 1925.
[6] B. Smilg, “The Instability of Pitching Oscillations of an Airfoil in Subsonic Incompressible Potential Flow”, J. Aeronaut. Sci. Vol.16, pp. 691-696, 1949.
[7] H. Cheilik, and H. Frissel “Theoretical Criteria for Single Degree of Freedom Flutter at Supersonic Speeds”, Cornell Aeronaut. Lab. Rept. CAL-7A, May 1947.
[8] H.L. Runyan, H. J. Cunningham, and C.E. Watkins “Theoretical Investigation of Several Types of Single-Degree-of-Freedom Flutter”, J. Aeronaut. Sci. Vol.19, pp.101-110, pp.126, 1952 (Comments by K.P. Abichandani and R.M. Rosenberg and author’s reply, 215-216; 503-504).
[9] H.J. Cunningham, “Analysis of Pure-Bending Flutter of a Cantilever Swept Wing and Its Relation to Bending-Torsion Flutter”, NACA Tech. Note pp. 2461, 1951.
[10] J.H. Greidanus, “Low-Speed Flutter”, J. Aeronaut. Sci. Vol.16, pp.127-128, 1949.
[11] J. Dugundji, “Theoretical consideration of Panel flutter at high supersonic Mach No.”, AIAA J., Vol.4, No.7, 1966.
[12] E.H. Dowell, “Nonlinear oscillation of a fluttering plate”, AIAA J. Vol.4, No.7, 1996.
[13] E.H. Dowell, “Theoretical and experimental panel flutter study”, AIAA J. Vol.3, No.12, 1995.
[14] J.B. Kosmatka, “Flexure-Torsion behavior of prismatic beam”, AIAA J. Vol.31, No.1, 1993.
[15] W. Libo, S. Long, C. Lei, W. Zhigang, Y. Chao, “Design and Analysis of a Wind Tunnel Test Model System for Gust Alleviation of Aeroelastic Aircraft”, (53rd AIAA/ASME/ASCE/AHS/ASC Structures), Structural Dynamics and Materials Conference, pp.23-26, Honolulu, Hawaii, April 2012.
[16] D. A. Neal, M. G. Good, C. O. Johnson, H.H. Robertshaw, W.H. Mason, D. J. Inman, “Design and Wind-Tunnel Analysis of a Fully Adaptive Aircraft Configuration”, (45th AIAA/ASME/ASCE/AHS/ASC Structures), Structural Dynamics & Materials Conference pp.19-22 Palm Springs, California, USA, April 2004.
[17] A.A. Omar, A. Kurban, “Design, Fabrication and Experimental Testing of IIUM Free Wing Unmanned Aerial Vehicle (IIUM-FWUAV)”, Australian Journal of Basic and Applied Sciences, 5(6): 381-389, 2011 ISSN 1991-8178.
[18] R. Samikkannu, “Wind Tunnel Flutter Testing of Composite T-Tail Model of a Transport Aircraft with Fuselage Flexibility”, Wind Tunnels and Experimental Fluid Dynamics Research, Prof. Jorge Colman Lerner (Ed.), ISBN: 978-953-307-623-2, In Tech, 2011.
[19] T. Strand, E.S. Levinsky, “Wind Tunnel Tests of a Free-Wing Tilt-Propeller V/Stol Airplane Model”, Aeronautical Research Report, October 1969.
[20] ZAERO Theoretical Manual, Version 8.5, ZONA 02 – 12.4, 2011.
[21] G. Gloth, M. Degener, U. Füllekrug, J. Gschwilm, M. Sinapius, P. Fargette, B. Levadoux, P. Lubrina, “New Ground Vibration Testing Techniques for Large Aircraft”, Sound and Vibration, Vol. 35, No. 11, pp. 14-18, 2001.
[22] D. Göge, M. Böswald, U. Füllekrug, P. Lubrina, “Ground Vibration Testing of Large Aircraft – State-of-the-Art and Future Perspectives”, IMAC 25 Int. Modal Analysis Conf., Orlando, FL, Feb. 2007.
[23] M. W. Kehoe, “A Historical Overview of Flight Flutter Testing”, NASA Technical Memorandum 4720, USA, October 1995.
[24] D.J. Ewins, “Modal Testing: Theory, Practice and Application”, Research Studies Press Ltd., Baldock, Hertfordshire, England, 2000.