ON PANEL FLUTTER IN THE PRESENCE OF A BOUNDARY LAYER
Abstract
The energy transfer from the uniform flow outside a boundary layer to a transverse surface wave at the boundary is calculated on the hypothesis that the boundary layer may be represented by an inviscid, approximately parallel shear flow. This energy transfer is found to consist of two components; the first is similar to that found previously for supersonic panel flutter in the absence of a boundary layer and is relatively diminished by the presence of the boundary layer; the second is intrinsic to the shear flow and is present whenever the surface wave speed is smaller than the free stream speed (whether subsonic or supersonic). The application of the results to actual flutter calculations is discussed and an example of a pressurized cylinder considered. It is concluded that the presence of a typical boundary layer may reduce the degree of instability for supersonic flutter of a long, monocoque shell by an order of magnitude, thereby providing a possible explanation of discrepancies between earlier theories (in which boundary layer effects were neglected) and observation. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 20, 1957
- Accession Number
- AD0605759
Entities
People
- John W. Miles