Hostname: page-component-cd9895bd7-fscjk Total loading time: 0 Render date: 2024-12-25T06:56:18.118Z Has data issue: false hasContentIssue false
  • English
  • Français

A Note on the Supersonic Panel Flutter of Oblique Clamped Plates

Published online by Cambridge University Press:  04 July 2016

A. Kornecki
A. Kornecki*
Affiliation:
Department of Aeronautical Engineering, Technion—Israel Institute of Technology, Haifa
Get access Rights & Permissions [Opens in a new window]

Extract

Recently, the effect of sweepback on the boundaries of supersonic panel flutter was studied in Ref. (1), (2) and (3), all of them dealing with rectangular plates.

The present note considers the problem of panel flutter boundary of plates in the shape of a parallelogram with all edges clamped.

It is assumed that Ackeret's theory of linearised two-dimensional supersonic aerodynamic loading gives an adequate approximation to the air forces for high Mach numbers.

The criterion of instability is the coalescence of frequencies.

A four-mode solution was obtained by means of Galerkin's method using first two streamwise and spanwise deflection modes. The results are represented in the form of diagrams for different aspect ratios (a/b) and sweep angles(ϕ).

Type
Technical Notes
Information
The Aeronautical Journal , Volume 68 , Issue 640 , April 1964 , pp. 270 - 271
Copyright
Copyright © Royal Aeronautical Society 1964

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1.Kordes, E.et al. Theoretical Flutter Analysis of Flat Rectangular Panels in Uniform Coplanar Flow With Arbitrary Direction. NASA TN D-1156, 1962.Google Scholar
2.Eisley, J. G.et al. Flutter of Thin Plates Under Shear and Normal Forces. AIAA Journal, Vol. 1, March 1963.Google Scholar
3.Calligeros, J. M. and Dugundji, J.Effects of Orthotropicity Orientation on Supersonic Panel Flutter. AIAA Journal, Vol. 1, September 1963. (Reader's forum.)Google Scholar
4.Hedgepeth, J. M.Flutter of Rectangular Simply Supported Panels at High Supersonic Speed. Journal of the Aeronautical Sciences, Vol. 24, August 1957.Google Scholar
5.Iguchi, S.Eine Loesung fuer die Berechnung der Biegsamen Rechtechigen Platten. Springer, Berlin, 1933.Google Scholar
6.Wittrick, W. H.Buckling of Oblique Plates with Clamped Edges Under Uniform Compression. The Aeronautical Quarterly, Vol. 4, February 1953.CrossRefGoogle Scholar